STC SA758GL

Number SA758GL This Certificate issued to

Part 25* of the Federal Aviation Regulations. (*In accordance with original certification requirements set forth in Type Certificate Data Sheet A1NM and additional Certification Basis on page 3)

Description of Type Design Change: Installation of BFGoodrich or Goodrich Emergency Evacuation Slide/Raft, BFGoodrich or Goodrich P/N 7A1394-( ), in accordance with BFGoodrich or Goodrich Drawing List Report No. 84-31-020, Revision 1, dated January 24, 1985, or subsequent FAA approved revisions, and BFGoodrich Report No. 85-31-004, no revision, dated February 6, 1985, or subsequent FAA approved revisions.

1. After installation door counterbalance operation should be inspected and adjusted if necessary in accordance with Boeing 767 Maintenance Manual 52-11-16, dated August 1, 1983, page 207 and 208.

2. BFGoodrich or Goodrich Emergency Evacuation Slide/Rafts, P/N 7A1394-( ), shall be maintained in accordance with BFGoodrich Overhaul Manuals 25-60-07, no revision, dated July 8, 1983, and BFGoodrich or Goodrich 25-63-03, no revision, dated August 19, 1983 or subsequent FAA approved revisions.

(Continued on Page 3)

The FAA will reissue the certificate in the name of the transferee and forward it to him.

Transfer the ownership of the Supplemental Type Certificate Number to (Name of transferee) (Address of transfer) (Number and street)

(City, State, and Zip code) from (Name of grantor) (Print or type) (Address of grantor) (Number and street)

(City, State, and Zip code) Extent of Authority (if licensing agreement):

Signature of grantor (In ink):

Number SA758GL

Date Amended: March 5, 1985; August 23, 1988; April 19, 2013 Date Reissued: April 30, 1987; October 24, 2001; March 12, 2002

Limitations and Conditions (Continued)

3. The approval of this change in type design applies to the above listed aircraft model(s) only.

This approval should not be incorporated in any aircraft unless it is determined that the interrelationship between this installation and any previous approved configuration will not introduce any adverse effect upon the airworthiness of the aircraft.

If the holder agrees to permit another person to use this certificate to alter the product, the holder shall give the other person written evidence of that permission.

Certification Basis

Based on 14 CFR §§ 21.115 and 21.101 for non-significant changes to type design, the certification basis for this change is as follows:

a) The certification basis for parts not changed or not affected by this change is in accordance with Type Certificate Data Sheet, A1NM.

b) The certification basis for parts changed or affected by this change is:

Regulations at the amendment level in TCDS A1NM

25.789, 25.812(g)(2), 25.812(h), 25.812(j), 25.853(b), 25.1359(d)

14 CFR Part 26 regulations

Based on 14 CFR §§ 21.101(g), applicable provisions of 14 CFR part 26 a re included in the certification basis. For any future 14 CFR part 26 amendments, the holder of this STC must demonstrate compliance with the applicable sections.

As of the issuance date of this STC, compliance has been found for the following regulations 14 CFR §§ 26.11, ( Admt No. 26- 0), 26.47, (Amdt No. 26- 1). The above 14 CFR part 26 certification basis is only applicable to Goodrich Drawing List Report No. 84- 31-020, Revision 16, dated January 23, 2013, or later FAA approved revisions.

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