This disclosure relates to an electromagnetic effect (“EME”) protection seal cap and more particularly to an EME protection seal cap which is employed to cover a portion of a fastener which extends from a surface within an aircraft to prevent sparking within the interior of the aircraft.
Current installation of EME protection seal caps, which cover an end portion of a fastener extending from a surface within an aircraft, requires much time, labor and cost and experiences a high rate of defective installations. Defective installation of an EME protection seal cap requires re-installation of the defectively installed protection seal cap whether during fabrication of the aircraft or during in-service maintenance of the aircraft. Since select aircraft utilize potentially thousands of EME protection seal caps, savings on installation and improvement on quality installations are of high value.
Regardless of fabrication of the aircraft or in-service maintenance of the aircraft, the EME protection seal caps will be inspected and if determined to not meet specifications, the EME protection seal caps will be scraped off and replaced. The replacement of the protection seal caps for in-service maintenance, which occur in the field, will experience installation of the protection seal caps within confined space within the aircraft in contrast to a controlled environment of a factory at time of fabrication of the aircraft. The installation of the EME protection seal cap requires the installer to hold the protection seal cap in place on a structure of the aircraft for approximately a minute while sealant, used in the installation of the protection seal cap, decompresses under the protection seal cap.
Without holding the protection seal cap in place during decompression of the sealant, the decompression of the sealant will cause liftoff of the protection seal cap with respect to the surface of the structure to which the protection seal cap is being secured. Liftoff of the protection seal cap is unacceptable and requires re-installation of the protection seal cap resulting in additional labor and cost.
There is a need to improve on the time expended for installation of protection seal caps including reducing the number of quality defects, which require re-installation of the protection seal cap. There is also a need to reduce the effort expended by the installer with respect to holding the protection seal cap during application of sealant and during decompression of the sealant, particularly in confined locations and also where installation orientations provide gravity challenges with respect to maintaining the protection seal cap in a desired position. In addition, there is a need to install a protection seal cap at the time of in-service maintenance wherein removal of all of the old sealant from the fastener is not required.
An example includes a protection seal cap for enclosing an end portion of a fastener which extends from a structure, which includes a cap member, which includes a sidewall that defines an interior space within the cap member. The sidewall forms a continuous wall member positioned within the cap member. The continuous wall member defines an opening providing access to the interior space. The continuous wall member is configured to create an interference compression fit between the end portion of the fastener and the continuous wall member.
An example includes a method for holding a protection seal cap against a structure and enclosing an end portion of a fastener which extends from the structure. The method includes positioning a cap member of the protection seal cap over the end portion of the fastener, wherein the cap member includes a sidewall which defines an interior space within the cap member. The sidewall forms a continuous wall member which defines an opening providing access to the interior space. The continuous wall member is configured to create an interference compression fit between the end portion of the fastener and the continuous wall member. The method further includes deforming of the continuous wall member creating an interference compression fit between the continuous wall member and the end portion of the fastener.
The features, functions, and advantages that have been discussed can be achieved independently in various embodiments or may be combined in yet other embodiments further details of which can be seen with reference to the following description and drawings.
In referring to
With respect to discussion related to continuous wall member 24, continuous wall member is designated as 24 in a non-deformed condition, as seen in
End portion 12 of fastener 14, in this example, includes a tool interface configuration 30, as seen in
As mentioned above, a head portion of end portion 12 of fastener 14 can take on a wide variety of configurations and sizes. Similarly, end portion 12 of fastener 14 can be positioned on an opposing side of fastener 14 and can take on one of a variety of configurations and sizes which include, for example, a wide variety of nut(s) (not shown) or a wide variety of nut(s) and washer(s) (also not shown). In applying cap member 18 to end portion 12 of fastener 14, cap member 18 can be used to engage either end portion 12 of fastener 14 as needed in fabrication or maintenance of an aircraft. Cap member 18 can be used to enclose end portion 12 of fastener 14 which includes the head portion of the fastener 14 as shown for example in
In the present example, opening 26, as seen in
As seen in
In this example, further deformation of continuous wall member 24′ occurs with deformation of the overall configuration or shape of continuous wall member 24′ which effects shape of opening 26 with end portion 12 of fastener 14 positioned within opening 26 surrounded by and in contact with continuous wall member 24′. The shape of continuous wall member 24′ becomes distorted as seen in
With deformation of continuous wall member 24′ at locations 34, 36 and 38 along with the distortion in shape of continuous wall member 24′, a compression interference fit is created between end portion 12 of fastener 14 and continuous wall member 24′ creating friction between continuous wall member 24′ and end portion 12 of fastener 14. With cap member 18 positioned against structure 16, the compression friction maintains cap member secured to fastener 14 and end portion 12 of fastener 14 enclosed within cap member 18. With continuous wall member 24′ gripping end portion 12 of fastener 14 by way of the interference compression and resulting friction, cap member 18 can be positioned and secured into any orientation onto structure 16 within an aircraft regardless of gravitational forces operating on cap member 18. This orientation can include extreme orientations of cap member 18 such as being positioned upside down on a surface, positioned on a vertical surface or positioned on an inclined surface without the individual installer needing to hold cap member 18 in place. The holding of cap member 18 in place, by way of the interference compression fit and maintaining end portion 12 of fastener 14 enclosed within cap member 18 and structure 16, as will be described below, cap member 18 is in proper position during injecting of sealant within cap member 18 facilitating installation of cap member 18 and in proper position during decompression of sealant without any need for the installer to hold cap member 18 in place providing enhanced rate of quality installations. Moreover, the compression fit capabilities of continuous wall member 24′ also provides installer the ability to not have to remove all sealant in an in-service maintenance of the aircraft. The compression interference fit will accommodate cap member 18 gripping end portion 12 of fastener 14 without all sealant being removed from the end portion 12 of fastener 14 and provide installer from needing to remove all sealant when installing of cap member 18.
In referring to
In referring to
As earlier discussed, fastener 14 is constructed of a harder material than that of the material which constructs continuous wall member 24, 24′ such that with a force applied by the end portion 12 of fastener 14 against continuous wall member 24 continuous wall member 24′ deforms. The deformation of continuous wall member 24, 24′ provides the interference compression fit between continuous wall member 24′ and end portion 12 of fastener 14 properly holding cap member 18 in position for sealant 62 injection to be accomplished and for decompression of sealant 62 to occur without cap member 18 experiencing unwanted liftoff of cap member 18 from structure 16.
In referring to
Positioning 66 of cap member 18 further includes positioning cap member 18 against structure 16. Sidewall 20 forms wall member 40 positioned spaced from continuous wall member 24. Wall member 40 extends about continuous wall member 24 and channel 44 defined by sidewall 20 is positioned between wall member 40 and continuous wall member 24. Wall member 40 defines two ports 46, 48 which extend through wall member 40 and are in fluid communication with channel 44. Method 64 further includes injecting sealant 62 into channel 44 through one of the two ports 46, 48.
While various embodiments have been described above, this disclosure is not intended to be limited thereto. Variations can be made to the disclosed embodiments that are still within the scope of the appended claims.
Number | Name | Date | Kind |
---|---|---|---|
1368637 | McFarland | Feb 1921 | A |
1868084 | Wheelwright | Jul 1932 | A |
2020522 | Seguin | Nov 1935 | A |
3241427 | Krell | Mar 1966 | A |
3699368 | Palmer | Oct 1972 | A |
4013190 | Wiggins et al. | Mar 1977 | A |
4295766 | Shaw | Oct 1981 | A |
4519974 | Bravenec et al. | May 1985 | A |
4630168 | Hunt | Dec 1986 | A |
4636446 | Lee | Jan 1987 | A |
4749321 | Knohl | Jun 1988 | A |
4826380 | Henry | May 1989 | A |
4850778 | Clough et al. | Jul 1989 | A |
4884933 | Preusker et al. | Dec 1989 | A |
5108853 | Feres | Apr 1992 | A |
5350266 | Espey et al. | Sep 1994 | A |
5752794 | Krawczak | May 1998 | A |
6053683 | Cabiran | Apr 2000 | A |
6102128 | Bridgeman | Aug 2000 | A |
6318942 | Wieczorek | Nov 2001 | B1 |
7134666 | Beyssac et al. | Nov 2006 | B2 |
7755876 | Morrill et al. | Jul 2010 | B2 |
7918081 | Schlichting et al. | Apr 2011 | B2 |
7936550 | Morrill et al. | May 2011 | B2 |
8318942 | Zhang | Nov 2012 | B2 |
8388293 | Hutter, III | Mar 2013 | B2 |
8711541 | Umemoto et al. | Apr 2014 | B2 |
8717735 | Day et al. | May 2014 | B2 |
8717736 | Asahara et al. | May 2014 | B2 |
8840740 | Rorabaugh et al. | Sep 2014 | B2 |
8894338 | Dobbin et al. | Nov 2014 | B2 |
9011062 | Chirol | Apr 2015 | B2 |
9133874 | Hill | Sep 2015 | B2 |
9188226 | Pajel et al. | Nov 2015 | B2 |
9228604 | Dobbin | Jan 2016 | B2 |
9764854 | Dobbin et al. | Sep 2017 | B2 |
10151337 | Hill | Dec 2018 | B2 |
10501202 | Roper et al. | Dec 2019 | B2 |
10655667 | Stevens et al. | May 2020 | B2 |
10729043 | Boettcher | Jul 2020 | B1 |
10920818 | Cowan et al. | Feb 2021 | B2 |
10948004 | Auffinger et al. | Mar 2021 | B2 |
10962043 | Stevens et al. | Mar 2021 | B2 |
10982704 | Auffinger et al. | Apr 2021 | B2 |
10989244 | Auffinger et al. | Apr 2021 | B2 |
11022164 | Roper et al. | Jun 2021 | B2 |
11078947 | Roper et al. | Aug 2021 | B2 |
11236777 | Stevens | Feb 2022 | B2 |
11571595 | Damazo et al. | Feb 2023 | B2 |
20020192052 | Ruspa | Dec 2002 | A1 |
20080137259 | Heeter et al. | Jun 2008 | A1 |
20090128983 | Hernandez | May 2009 | A1 |
20090194297 | Ortiz Teruel | Aug 2009 | A1 |
20100303582 | Choi et al. | Dec 2010 | A1 |
20120217673 | Hutter, III | Aug 2012 | A1 |
20130206759 | Wurz et al. | Aug 2013 | A1 |
20130223951 | Bessho et al. | Aug 2013 | A1 |
20130322982 | Dobbin | Dec 2013 | A1 |
20140048198 | Dobbin et al. | Feb 2014 | A1 |
20140261956 | Wiseman et al. | Sep 2014 | A1 |
20140341675 | Dobbin | Nov 2014 | A1 |
20140373359 | Schomaker et al. | Dec 2014 | A1 |
20150060465 | Limbacher et al. | Mar 2015 | A1 |
20150082603 | Rawdon et al. | Mar 2015 | A1 |
20150086295 | Cameron et al. | Mar 2015 | A1 |
20150184688 | Dobbin et al. | Jul 2015 | A1 |
20150345533 | Hill | Dec 2015 | A1 |
20160076577 | Rizzello | Mar 2016 | A1 |
20160131179 | Prouty et al. | May 2016 | A1 |
20160159493 | Dobbin | Jun 2016 | A1 |
20160195125 | Dobbin | Jul 2016 | A1 |
20160245330 | Dobbin | Aug 2016 | A1 |
20170021209 | Damazo et al. | Jan 2017 | A1 |
20170050746 | Dobbin | Feb 2017 | A1 |
20170082131 | Bessho et al. | Mar 2017 | A1 |
20190241276 | Dobbin | Aug 2019 | A1 |
20190301515 | Dobbin | Oct 2019 | A1 |
20210164513 | Cowan et al. | Jun 2021 | A1 |
20210190124 | Stevens et al. | Jun 2021 | A1 |
Number | Date | Country |
---|---|---|
2856687 | Mar 2015 | CA |
2858461 | Mar 2015 | CA |
105408642 | Mar 2016 | CN |
105473445 | Apr 2016 | CN |
107298182 | Oct 2017 | CN |
107448463 | Dec 2017 | CN |
1085586 | Jul 1960 | DE |
2610506 | Jul 2013 | EP |
2698318 | Feb 2014 | EP |
2713065 | Apr 2014 | EP |
2812248 | Dec 2014 | EP |
2860410 | Apr 2015 | EP |
2860411 | Apr 2015 | EP |
2996941 | Mar 2016 | EP |
3027917 | Jun 2016 | EP |
3059170 | Aug 2016 | EP |
3106380 | Dec 2016 | EP |
3287362 | Feb 2018 | EP |
3462046 | Apr 2019 | EP |
3546374 | Oct 2019 | EP |
612381 | Nov 1948 | GB |
H02102910 | Apr 1990 | JP |
H03125911 | Dec 1991 | JP |
H08-145032 | Jun 1996 | JP |
2000039010 | Feb 2000 | JP |
2001165138 | Jun 2001 | JP |
2002266832 | Sep 2002 | JP |
2004169853 | Jun 2004 | JP |
2014128760 | Feb 2016 | RU |
WO-9729289 | Aug 1997 | WO |
WO-0057069 | Sep 2000 | WO |
WO-2009063063 | May 2009 | WO |
WO-2012147645 | Nov 2012 | WO |
WO-2012170672 | Dec 2012 | WO |
WO-2013117756 | Aug 2013 | WO |
WO-2013178985 | Dec 2013 | WO |
WO-2014118117 | Aug 2014 | WO |
WO-2014118510 | Aug 2014 | WO |
WO-2014184722 | Nov 2014 | WO |
WO-2015015153 | Feb 2015 | WO |
WO-2015025130 | Feb 2015 | WO |
Entry |
---|
Extended EP Search Report for EP Application No. 19204019.4 dated Mar. 30, 2020. |
Written Opinion for EP Application No. 19204019.4 dated Mar. 30, 2020. |
Extended European Search Report for EP Application No. 21161373.2 dated Jul. 21, 2021. |
Color Photographs of Boeing Proprietary, Zap Cap Further Screening Test Plan for 787 Fuel Tank Use, Mar. 24, 2016, 2 pg. |
Extended European Search Report for EP Application No. 20176033.7 dated Oct. 23, 2020. |
Drawings of Boeing Part Standard, BACC50AP, dated Feb. 2, 2017, 2 pgs. |
Photographs of Boeing Proprietary, Zap Cap Further Screening Test Plan for 787 Fuel Tank Use, Mar. 24, 2016, 1 pg. |
http://www.ppgaerospace.com/getmedia/9a234ec3-1db9-48de-94f7-c212ac2ba705/SealCapFlyer.pdf.aspx, PPG Aerospace PRC Seal Caps, retrieved Sep. 7, 2016. |
http://www.porex.com/files/documents/Porex-Battery-Vents-Letter—English, Porex Battery Vents, 2013. |
Extended European Search Report for foreign counterpart EP Application No. 16173069, dated Nov. 17, 2016. |
Product Literature for ERG Duocel Aluminum Foam, downloaded from ERO Aerospace website, www.ergaerospace.com/literature/erg_duocel.pdf, Jul. 9, 2015. |
“HRL Researchers Develop World's Lightest Material,” downloaded from HRL Laboratories website, www.hrl.com/hrlDocs/pressreleases/2011/prsRls_111117, Jul. 10, 2015. |
Daniel J. Cowan et al., U.S. Appl. No. 15/964,340, filed Apr. 27, 2018. |
Bart Stevens et al., U.S. Appl. No. 15/718,618, filed Sep. 28, 2017. |
Sean Auffinger et al., U.S. Appl. No. 16/046,316, filed Jul. 26, 2018. |
Bart Stevens et al., U.S. Appl. No. 15/960,835, filed Apr. 24, 2018. |
Toulouse, Mixed Metal-Composite Assembly, May 2013. |
Hutchinson Proprietary Document, Accessories: TP Nutcaps, 1 page. |
Click Bond Cap dated May 16, 2016, 4 pgs. |
Extended European Search Report for EP Application No. 18196707.6 dated Feb. 19, 2019. |
EP Search Report for Application No. EP14175808 dated Mar. 6, 2015. |
Prc-Desoto International, Inc., “Technical Data Sheet Aerospace Sealants Customized Sealant Solutions PRC(R) Seal Caps,” May 1, 2017, Lit, #4086, Sylmar, CA, pp. 1-2; retrieved on Dec. 4, 2018, retrieved from internet: http://www.ppgaerospace.com/getmedia/9a234ec3-1db9-48de-94f7-c212ac2ba705/SealCapFlyer.pdf.aspx. |
Porex Corporation, “Porex(R) Battery Vents—Flame Arrestors,” Porex Advanced Porous Materials, PXT-621-080513-00, Jan. 1, 2013, pp. 1-2, retrieved on Dec. 4, 2018, retrieved from internet: http://www.porex.com//files/documents/POREX-Battery-Vents-Letter-for-Web.pdf. |
“Customized Sealants Solutions: PRC® Seal Caps,” PPG Aerospace, product literature downloaded from ppaerospace.com on Sep. 7, 2016. |
“HRL Researchers Develop World's Lightest Material,” downloaded from HRL Laboratories website, HRL.com on Jul. 10, 2015. |
“ERG Duocel® aluminum foam,” product literature downloaded from ERG Aerospace website, ERGaerospace.com on Jul. 9, 2015. |
Office Action for RU Application No. 2018127328/07 dated May 20, 2019. |
EP Search Report for EP Application No. 19167831.7 dated Aug. 29, 2019. |
EP Search Report for Application No. EP19166688 dated Aug. 29, 2019. |
EP Office Action for Application No. 19166688.2 dated Sep. 20, 2019. |
European Search Report for Application No. 19179944.4 dated Sep. 10, 2019. |
Communication Pursuant to Article 94(3) dated Oct. 16, 2019. |
Office Action for CA Application No. 3,038,285 dated May 12, 2022. |
Notification of Second Office Action for CN Application No. 2019103416596 dated Jul. 19, 2022. |
Extended EP Search Report for EP Application No. 19207962.2 dated Mar. 26, 2020. |
Communication Pursuant to Article 94(3) EPC for EP Application No. 19167831.7 dated Feb. 23, 2022. |
First Office Action for CN Application No. 2019103311537 dated Feb. 22, 2022. |
Search Report for CN Application No. 2019103311537 dated Feb. 22, 2022. |
Notification of First Office Action for CN Application No. 2019103416596 dated Mar. 7, 2022. |
Extended European Search Report for EP Application No. 22152477.0 dated Apr. 21, 2022. |
European Search Report for EP Application No. EP19217717 dated May 8, 2020. |
Number | Date | Country | |
---|---|---|---|
20210285481 A1 | Sep 2021 | US |