71586 Federal Register / Vol. 81, No. 201 / Tuesday, October 18, 2016 / Rules and Regulations 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–3629; Directorate 

Identifier 2015–NM–011–AD; Amendment 

39–18662; AD 2016–19–13] 

RIN 2120–AA64 

Airworthiness Directives; Dassault 

Aviation Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Dassault Aviation Model MYSTERE– 

FALCON 50, MYSTERE–FALCON 900, 

FALCON 900EX, FALCON 2000, and 

FALCON 2000EX airplanes. This AD 

was prompted by a report of an in-flight 

lightning strike to the WHELEN anticollision light located on the top of the 

vertical fin tip that caused severe 

damage and resulted in the loss of some 

airplane functions. This AD requires 

modification of the anti-collision light 

bonding. We are issuing this AD to 

prevent loss of electrical power and 

essential airplane functions, and 

possible reduced control of the airplane. 

DATES: This AD is effective November 

22, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of November 22, 2016. 

ADDRESSES: For service information 

identified in this final rule, contact 

Dassault Falcon Jet Corporation, 

Teterboro Airport, P.O. Box 2000, South 

Hackensack, NJ 07606; telephone 201– 

440–6700; Internet http://

www.dassaultfalcon.com. You may 

view this referenced service information 

at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., 

Renton, WA. For information on the 

availability of this material at the FAA, 

call 425–227–1221. It is also available 

on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

3629. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

3629; or in person at the Docket 

Management Facility between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Office (telephone 800–647– 

5527) is Docket Management Facility, 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue SE., 

Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: Tom 

Rodriguez, Aerospace Engineer, ANM– 

116, Transport Airplane Directorate, 

FAA, 1601 Lind Avenue SW., Renton, 

WA 98057–3356; telephone 425–227– 

1137; fax 425–227–1139. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a supplemental notice of 

proposed rulemaking (SNPRM) to 

amend 14 CFR part 39 by adding an AD 

that would apply to certain Dassault 

Aviation Model MYSTERE–FALCON 

50, MYSTERE–FALCON 900, FALCON 

900EX, FALCON 2000, and FALCON 

2000EX airplanes. The SNPRM 

published in the Federal Register on 

June 17, 2016 (81 FR 39597) (‘‘the 

SNPRM’’). We preceded the SNPRM 

with a notice of proposed rulemaking 

(NPRM) that published in the Federal 

Register on September 24, 2015 (80 FR 

57545) (‘‘the NPRM’’). The NPRM 

proposed to require modification of the 

anti-collision light bonding. The NPRM 

was prompted by a report of an in-flight 

lightning strike to the WHELEN anticollision light located on the top of the 

vertical fin tip that caused severe 

damage and induced the loss of some 

airplane functions. The SNPRM 

proposed to clarify the applicability. We 

are issuing this AD to prevent loss of 

electrical power and essential airplane 

functions, and possible reduced control 

of the airplane. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2015–0006, dated January 15, 

2015 (referred to after this as the 

Mandatory Continuing Airworthiness 

Information, or ‘‘the MCAI’’), to correct 

an unsafe condition for certain Dassault 

Aviation Model MYSTERE–FALCON 

50, MYSTERE–FALCON 900, FALCON 

900EX, FALCON 2000, and FALCON 

2000EX airplanes. The MCAI states: 

An occurrence was reported where a 

Falcon 2000 aeroplane experienced an inflight lightning strike, which caused severe 

damage and induced the loss of some 

aeroplane functions. The investigation results 

revealed that the entering point of the 

lightning was at the WHELEN anti-collision 

light located on the top of the vertical fin tip. 

When the lightning strike hit the anticollision light, an electric arc occurred 

between the aeroplane structure and the anticollision light and created a conductive path 

by which the lightning current entered inside 

the aeroplane. Further analysis has 

determined that the electrical bonding 

between the WHELEN anti-collision light, 

Part Number (P/N) 01–0790044–09, and the 

fin tip fairing or the No. 2 engine air intake 

cover is insufficient to withstand a lightning 

strike. 

In case of severe lightning, this condition, 

if not corrected, could lead to an unsafe 

condition (loss of electrical power and/or of 

essential functions) possibly resulting in 

reduced control of the aeroplane. 

To address this potential unsafe condition, 

Dassault Aviation developed a modification 

(mod) to improve the WHELEN anti-collision 

light bonding when the anti-collision light is 

located on top of the vertical fin tip or on No. 

2 engine air intake cover, and issued several 

Service Bulletins (SB) to modify all affected 

aeroplanes in service. 

For the reasons described above, this 

[EASA] AD requires modification of the anticollision light bonding. 

You may examine the MCAI in the AD 

docket on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

3629. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the SNPRM or 

on the determination of the cost to the 

public. 

Conclusion 

We reviewed the relevant data and 

determined that air safety and the 

public interest require adopting this AD 

as proposed except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the SNPRM for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the SNPRM. 

Related Service Information Under 1 

CFR Part 51 

We reviewed the following service 

information. 

• Dassault Service Bulletin F50–481, 

Revision 1 (also referred to as 481–R1), 

dated January 26, 2015. 

• Dassault Service Bulletin F900–372, 

Revision 1 (also referred to as 372–R1), 

dated January 26, 2015. 

• Dassault Service Bulletin F900–378, 

Revision 1 (also referred to as 378–R1), 

dated January 26, 2015. 

• Dassault Service Bulletin F900EX– 

285, Revision 1 (also referred to as 285– 

R1), dated January 26, 2015. 


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• Dassault Service Bulletin F900EX– 

305, Revision 1 (also referred to as 305– 

R1), dated January 26, 2015. 

• Dassault Service Bulletin F2000– 

337, Revision 1 (also referred to as 337– 

R1), dated January 26, 2015. 

• Dassault Service Bulletin F2000EX– 

108, Revision 1 (also referred to as 108– 

R1), dated January 26, 2015. 

The service information describes 

procedures for modifying the anticollision light bonding. These 

documents are distinct since they apply 

to different airplane models in different 

configurations. This service information 

is reasonably available because the 

interested parties have access to it 

through their normal course of business 

or by the means identified in the 

ADDRESSES section. 

Costs of Compliance 

We estimate that this AD affects 778 

airplanes of U.S. registry. 

We also estimate that it would take 

about 12 work-hours per product to 

comply with the basic requirements of 

this AD. The average labor rate is $85 

per work-hour. Required parts would 

cost about $801 per product. Based on 

these figures, we estimate the cost of 

this AD on U.S. operators to be 

$1,416,738, or $1,821 per product. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this AD will not 

have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under the 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); 

3. Will not affect intrastate aviation in 

Alaska; and 

4. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

2016–19–13 Dassault Aviation: 

Amendment 39–18662; Docket No. 

FAA–2015–3629; Directorate Identifier 

2015–NM–011–AD. 

(a) Effective Date 

This AD is effective November 22, 2016. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Dassault Aviation 

airplanes, certificated in any category, 

identified in figure 1 to paragraph (c) of this 

AD. 

FIGURE 1 TO PARAGRAPH (c) OF THIS AD—APPLICABILITY

Airplanes Configuration 

Except airplanes modified through: 1

Dassault modification 

embodied in 

production 

Service bulletin in 

service 

Dassault Aviation Model MYSTERE-FALCON 

50 airplanes.

M1853 has been embodied in production or 

in service through Dassault Service Bulletin 

F50–241.

M2083 or M3094 2 ...... Dassault Service Bulletin F50-257. 

Dassault Aviation Model MYSTERE-FALCON 

900 airplanes.

Group 1: M1682 has been embodied in production or in service through Dassault 

Service Bulletin F900–182 3.

M5381 ........................ Not applicable. 

Group 2: M1682 has been embodied in production or in service through Dassault 

Service Bulletin F900–182 and Modification 

M1947 is embodied in production or in 

service through Dassault Service Bulletin 

F900–176 4.

M5386 ........................ Not applicable. 

Dassault Aviation Model FALCON 900EX airplanes.Group 1: M1682 has been embodied in production or in service through Dassault 

Service Bulletin F900EX-025 3.

M5381 ........................ Not applicable. 

Group 2: M1682 has been embodied in production or in service through Dassault 

Service Bulletin F900EX-025 and Modification M1947 is embodied in production or in 

service through Dassault Service Bulletin 

F900EX-19 4.

M5103 or M5386 ........ Not applicable. 


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71588 Federal Register / Vol. 81, No. 201 / Tuesday, October 18, 2016 / Rules and Regulations 

FIGURE 1 TO PARAGRAPH (c) OF THIS AD—APPLICABILITY—Continued 

Airplanes Configuration 

≤Except airplanes modified through: 1

Dassault modification 

embodied in production 

Service bulletin in 

service 

Dassault Aviation Model FALCON 2000 airplanes.M331 has been embodied in production or in 

service through Dassault Service Bulletin 

F2000–44.

M810 or M1061 or 

M2778.

Dassault Service Bulletin F2000–111. 

Dassault Aviation Model FALCON 2000EX airplanes.M1802 has been embodied in production ...... M810 or M1061 or 

M2778.

Not applicable. 

1The excluded airplanes, as specified in figure 1 to paragraph (c) of this AD—Applicability, embody either one modification in production or 

one service bulletin in service, as applicable. 2 Modification M2083, Dassault Service Bulletin F50–257, Modification M1947, Dassault Service Bulletin F900–176, Dassault Service Bulletin 

F900EX–19, Modification M5103, as applicable, introduce fin tip SATCOM fairing, in production or in service. 3Group 1: Airplanes with WHELEN anti-collision light located on top of the vertical fin tip. 

4Group 2: Airplanes with WHELEN anti-collision light located on top of the engine No. 2 air intake cover. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 33, Lights. 

(e) Reason 

This AD was prompted by a report of an 

in-flight lightning strike to the WHELEN anticollision light located on the top of the 

vertical fin tip that caused severe damage and 

resulted in the loss of some airplane 

functions. We are issuing this AD to prevent 

loss of electrical power and essential airplane 

functions, and possible reduced control of 

the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Modification 

Within 24 months after the effective date 

of this AD, modify the anti-collision light 

bonding, in accordance with the 

Accomplishment Instructions of the 

applicable service information specified in 

paragraphs (g)(1) through (g)(7) of this AD. 

(1) For Model MYSTERE–FALCON 50 

airplanes: Dassault Service Bulletin F50–481, 

Revision 1 (also referred to as 481–R1), dated 

January 26, 2015. 

(2) For Model MYSTERE–FALCON 900 

airplanes with the WHELEN system installed 

on the vertical fin tip: Dassault Service 

Bulletin F900–372, Revision 1 (also referred 

to as 372–R1), dated January 26, 2015. 

(3) For Model MYSTERE–FALCON 900 

airplanes with the WHELEN system installed 

on the S-duct cowl: Dassault Service Bulletin 

F900–378, Revision 1 (also referred to as 

378–R1), dated January 26, 2015. 

(4) For Model FALCON 900EX airplanes 

with the WHELEN system installed on the 

vertical fin tip: Dassault Service Bulletin 

F900EX–285, Revision 1 (also referred to as 

285–R1), dated January 26, 2015. 

(5) For Model FALCON 900EX airplanes 

with the WHELEN system installed on the Sduct cowl: Dassault Service Bulletin 

F900EX–305, Revision 1 (also referred to as 

305–R1), dated January 26, 2015. 

(6) For Model FALCON 2000 airplanes: 

Dassault Service Bulletin F2000–337, 

Revision 1 (also referred to as 337–R1), dated 

January 26, 2015. 

(7) For Model FALCON 2000EX airplanes: 

Dassault Service Bulletin F2000EX–108, 

Revision 1 (also referred to as 108–R1), dated 

January 26, 2015. 

(h) Credit for Previous Actions 

This paragraph provides credit for actions 

required by paragraph (g) of this AD, if those 

actions were performed before the effective 

date of this AD using the applicable service 

information identified in paragraphs (h)(1) 

through (h)(7) of this AD. 

(1) For Model MYSTERE–FALCON 50 

airplanes: Dassault Service Bulletin F50–481, 

dated August 22, 2007. 

(2) For Model MYSTERE–FALCON 900 

airplanes with the WHELEN system installed 

on the vertical fin tip: Dassault Service 

Bulletin F900–372, dated August 22, 2007. 

(3) For Model MYSTERE–FALCON 900 

airplanes with the WHELEN system installed 

on the S-duct cowl: Dassault Service Bulletin 

F900–378, dated September 19, 2007. 

(4) For Model FALCON 900EX airplanes 

with the WHELEN system installed on the 

vertical fin tip: Dassault Service Bulletin 

F900EX–285, dated July 18, 2007. 

(5) For Model FALCON 900EX airplanes 

with the WHELEN system installed on the Sduct cowl: Dassault Service Bulletin 

F900EX–305, dated September 19, 2007. 

(6) For Model FALCON 2000 airplanes: 

Dassault Service Bulletin F2000–337, dated 

July 25, 2007. 

(7) For Model FALCON 2000EX airplanes: 

Dassault Service Bulletin F2000EX–108, 

dated July 25, 2007. 

(i) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2015–0006, dated 

January 15, 2015, for related information. 

This MCAI may be found in the AD docket 

on the Internet at http://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2015–3629. 

(2) Contacting the Manufacturer: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer, the action must 

be accomplished using a method approved 

by the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

the EASA; or Dassault Aviation’s EASA 

Design Organization Approval (DOA). If 

approved by the DOA, the approval must 

include the DOA-authorized signature. 

(j) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2015–0006, dated 

January 15, 2015, for related information. 

This MCAI may be found in the AD docket 

on the Internet at http://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2015–3629. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (k)(3) and (k)(4) of this AD. 

(k) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless this AD specifies otherwise. 

(i) Dassault Service Bulletin F50–481, 

Revision 1 (also referred to as 481–R1), dated 

January 26, 2015. 

(ii) Dassault Service Bulletin F900–372, 

Revision 1 (also referred to as 372–R1), dated 

January 26, 2015. 

(iii) Dassault Service Bulletin F900–378, 

Revision 1 (also referred to as 378–R1), dated 

January 26, 2015. 

(iv) Dassault Service Bulletin F900EX–285, 

Revision 1 (also referred to as 285–R1), dated 

January 26, 2015. 

(v) Dassault Service Bulletin F900EX–305, 

Revision 1 (also referred to as 305–R1), dated 

January 26, 2015. 

(vi) Dassault Service Bulletin F2000–337, 

Revision 1 (also referred to as 337–R1), dated 

January 26, 2015. 

(vii) Dassault Service Bulletin F2000EX– 

108, Revision 1 (also referred to as 108–R1), 

dated January 26, 2015. 

(3) For service information identified in 

this AD, contact Dassault Falcon Jet 

Corporation, Teterboro Airport, P.O. Box 

2000, South Hackensack, NJ 07606; 

telephone 201–440–6700; Internet http://

www.dassaultfalcon. 


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(4) You may view this service information 

at the FAA, Transport Airplane Directorate, 

1601 Lind Avenue SW., Renton, WA. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

(5) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on 

September 14, 2016. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–22832 Filed 10–17–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2016–3703; Directorate 

Identifier 2015–NM–115–AD; Amendment 

39–18669; AD 2016–20–03] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

The Boeing Company Model 767–200, 

–300, and –400ER series airplanes. This 

AD was prompted by an evaluation by 

the design approval holder (DAH) 

indicating that the skin lap splice is 

subject to widespread fatigue damage 

(WFD). This AD requires repetitive 

external detailed and surface high 

frequency eddy current (HFEC) 

inspections of the outer skin for 

cracking around fastener heads common 

to the inboard fastener row of the skin 

lap splice and corrective action. We are 

issuing this AD to detect and correct 

fatigue cracking of the skin lap splice, 

which could grow and result in possible 

rapid decompression and reduced 

structural integrity of the airplane. 

DATES: This AD is effective November 

22, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of November 22, 2016. 

ADDRESSES: For service information 

identified in this final rule, contact 

Boeing Commercial Airplanes, 

Attention: Data & Services Management, 

P. O. Box 3707, MC 2H–65, Seattle, WA 

98124–2207; telephone: 206–544–5000, 

extension 1; fax: 206–766–5680; Internet 

https://www.myboeingfleet.com. You 

may view this referenced service 

information at the FAA, Transport 

Airplane Directorate, 1601 Lind Avenue 

SW., Renton, WA. For information on 

the availability of this material at the 

FAA, call 425–227–1221. It is also 

available on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2016– 

3703. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2016– 

3703; or in person at the Docket 

Management Facility between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (phone: 800–647–5527) is 

Docket Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Wayne Lockett, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office 

(ACO), 1601 Lind Avenue SW., Renton, 

WA 98057–3356; phone: 425–917–6447; 

fax: 425–917–6590; email: 

wayne.lockett@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to certain The Boeing Company 

Model 767–200, –300, and –400ER 

series airplanes. The NPRM published 

in the Federal Register on February 25, 

2016 (81 FR 9367) (‘‘the NPRM’’). The 

NPRM was prompted by an evaluation 

by the DAH indicating that the skin lap 

splice is subject to WFD. The NPRM 

proposed to require repetitive external 

detailed and surface HFEC inspections 

of the outer skin for cracking around 

fastener heads common to the inboard 

fastener row of the skin lap splice. We 

are issuing this AD to detect and correct 

fatigue cracking of the skin lap splice, 

which could grow and result in possible 

rapid decompression and reduced 

structural integrity of the airplane. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the NPRM and the FAA’s 

response to each comment. Boeing 

stated that it supports the NPRM. 

Effect of Winglets on Accomplishment 

of the Proposed Actions 

Aviation Partners Boeing stated that 

accomplishing the supplemental type 

certificate (STC) ST01920SE does not 

affect the actions specified in the 

NPRM. 

We concur with the commenter. We 

have redesignated paragraph (c) of this 

AD as (c)(1) and added new paragraph 

(c)(2) to this AD to state that installation 

of STC ST01920SE does not affect the 

ability to accomplish the actions 

required by this final rule. Therefore, for 

airplanes on which STC ST01920SE is 

installed, a ‘‘change in product’’ 

alternative method of compliance 

(AMOC) approval request is not 

necessary to comply with the 

requirements of 14 CFR 39.17. 

Request To Revise the Compliance 

Time for the Repetitive Inspection 

Intervals 

United Airlines (UAL) requested that 

we revise the repetitive inspection 

intervals for any repair accomplished 

using the structural repair manual 

(SRM) specified in Part 2 of Boeing 

Alert Service Bulletin 767–53A0260, 

dated August 26, 2014. UAL commented 

that a Zone B repair is Category B, and 

per the SRM inspections, the airplanes 

would have an initial inspection at 

25,000 total flight cycles after airplane 

delivery. UAL stated that the initial 

inspection compliance time for the 

proposed rule is 40,000 total flight 

cycles, and if a repair is accomplished 

at this time, it is already over the initial 

inspection threshold specified in the 

SRM. 

We agree with the commenter’s 

request. There is a conflict between the 

initial inspection thresholds in Boeing 

Alert Service Bulletin 767–53A0260, 

dated August 26, 2014, and the Category 

B repair specified in the SRM. We are 

working with Boeing to revise the 

conflicting compliance times for the 

SRM repairs. We have added a new 

paragraph (h) in this AD, which 

provides clarification that the postrepair damage tolerance inspections are 

not required by this AD, but are 

airworthiness limitations (ALIs), and 

those inspections are required by 

maintenance and operational rules. Any 

deviation from the post-repair ALI 

inspections will need FAA approval, 


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