Federal Register / Vol. 81, No. 154 / Wednesday, August 10, 2016 / Rules and Regulations 52755 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the International Branch, send it to ATTN: 

Tom Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1137; fax 425–227–1149. 

Information may be emailed to: 9-ANM-116- 

AMOC-REQUESTS@faa.gov. 

(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 

EASA; or Dassault Aviation’s EASA DOA. If 

approved by the DOA, the approval must 

include the DOA-authorized signature. 

(l) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA AD 

2015–0095, dated May 29, 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–2016–5464. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

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

(m) 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) Chapter 5–40–00, Airworthiness 

Limitations, DGT 107838, Revision 4, dated 

February 2, 2015, of the Dassault Aviation 

Falcon 7X Maintenance Manual. 

(ii) Reserved. 

(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.com. 

(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 July 27, 

2016. 

Victor Wicklund, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–18488 Filed 8–9–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–8429; Directorate 

Identifier 2015–NM–122–AD; Amendment 

39–18608; AD 2016–16–10] 

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 747–100, 

747–100B, 747–100B SUD, 747–200B, 

747–200C, 747–200F, 747–300, 747– 

400, 747–400D, 747–400F, 747SR, and 

747SP series airplanes. This AD was 

prompted by reports of fatigue cracks in 

the station 320 crown frame and in 

window post number 3. This AD 

requires repetitive inspections for cracks 

and missing fasteners of the station 320 

crown frame, cracks in the web and 

flange surfaces of the forward segment 

of window post number 3, and missing 

fasteners and cracks of the window 

upper sill; post-modification 

inspections for cracks of the window 

upper sill; a one-time fastener rework; 

and related investigative and corrective 

actions if necessary. We are issuing this 

AD to detect and correct fatigue 

cracking and missing fasteners of the 

station 320 crown frame, cracking of the 

window post number 3, and cracking of 

the window upper sill, which could 

result in an in-flight decompression and 

a loss of structural integrity of the 

fuselage. 

DATES: This AD is effective September 

14, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of September 14, 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–2015– 

8429. 

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– 

8429; 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: Bill 

Ashforth, Aerospace Engineer, Airframe 

Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office (ACO), 1601 

Lind Avenue SW., Renton, WA 98057– 

3356; phone: 425–917–6432; fax: 425– 

917–6590; email: Bill.Ashforth@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 747–100, 747–100B, 747–100B 

SUD, 747–200B, 747–200C, 747–200F, 

747–300, 747–400, 747–400D, 747– 

400F, 747SR, and 747SP series 

airplanes. The NPRM published in the 

Federal Register on January 13, 2016 

(81 FR 1577) (‘‘the NPRM’’). The NPRM 

was prompted by reports of fatigue 

cracks in the station 320 crown frame 

and in window post number 3. The 

NPRM proposed to require repetitive 

inspections for cracks and missing 

fasteners of the station 320 crown frame, 

cracks in the web and flange surfaces of 

the forward segment of window post 

number 3, and missing fasteners and 

cracks of the window upper sill; postmodification inspections for cracks of 

the window upper sill; a one-time 

fastener rework; and related 

investigative and corrective actions if 

necessary. We are issuing this AD to 

detect and correct fatigue cracking and 


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missing fasteners of the station 320 

crown frame, cracking of the window 

post number 3, and cracking of the 

window upper sill, which could result 

in an in-flight decompression and a loss 

of structural integrity of the fuselage. 

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. 

Request for Restoration Procedures 

United Airlines (UAL) requested that 

figure 21 in Boeing Alert Service 

Bulletin 747–53A2862, Revision 1, 

dated July 24, 2015, be revised to 

provide airplane maintenance manual 

references on reinstallation of the panels 

and all disturbed air conditioning 

systems, and to include operational 

check procedures of all the disturbed 

systems. 

We partially agree with UAL’s 

comment. We agree that figure 21 in 

Boeing Alert Service Bulletin 747– 

53A2862, Revision 1, dated July 24, 

2015, should provide robust access/

restoration procedures. We disagree 

with delaying this AD until any needed 

changes to figure 21 have been 

incorporated. Figure 21 is not a 

‘‘Required for Compliance’’ (RC) section 

of the service information and is not 

mandated by this AD. Therefore, 

operators can deviate from these 

instructions, as specified in paragraph 

(k)(4)(ii) of this AD. We have not 

changed this AD in this regard. 

Request To Revise Discussion Section of 

the NPRM 

Boeing requested that we revise the 

second sentence in the Discussion 

section of the NPRM, which states: 

‘‘Other Model 747 airplanes, except 

Model 747–8F and 747–8 airplanes, are 

of a similar station 320 crown frame 

configuration.’’ Boeing asked that the 

reference to Model 747–8F and Model 

747–8 airplanes be removed. Boeing 

stated that although having a different 

design, Model 747–8F and Model 747– 

8 airplanes have a similar station 320 

crown frame configuration as the other 

Model 747 airplanes. Boeing explained 

that, for Model 747–8F and Model 747– 

8 airplanes, it has issued service 

information that specifies repetitive 

inspections for cracking of the station 

320 crown frame and is mandated by 

certain airworthiness limitations 

(AWLs). 

We agree to clarify the Discussion 

section of the NPRM. We agree that 

Boeing Model 747–100, –200, –300, and 

–400 airplanes, and Model 747–8F and 

Model 747–8 airplanes, have similar 

station 320 crown frame configurations. 

However, we cannot revise the second 

sentence in the Discussion section of the 

NPRM because that particular sentence 

is not restated in the Discussion section 

of this AD. Also, as Boeing stated, the 

identified condition on Model 747–8F 

and Model 747–8 airplanes is addressed 

with AWLs. This AD addresses the 

identified unsafe condition on Model 

747–100, 747–100B, 747–100B SUD, 

747–200B, 747–200C, 747–200F, 747– 

300, 747–400, 747–400D, 747–400F, 

747SR, and 747SP series airplanes. We 

have not changed this AD in this regard. 

Clarification of Repetitive Inspections 

Required by Paragraph (h) of This AD 

We revised paragraph (h) of this AD, 

which refers to inspections specified in 

paragraphs (g)(1) through (g)(5) of this 

AD, by removing the text ‘‘for cracking 

in the window upper sill.’’ That text 

only applies to the inspection specified 

in paragraph (g)(5) of this AD and not 

to the inspections specified in 

paragraphs (g)(1) through (g)(4) of this 

AD. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, 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 NPRM for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM. 

Related Service Information Under 1 

CFR Part 51 

We reviewed Boeing Alert Service 

Bulletin 747–53A2862, Revision 1, 

dated July 24, 2015. The service 

information describes procedures for 

inspections and corrective actions for 

cracks and missing fasteners in the 

inner chord and outboard webs of the 

station 320 crown frame, in the left and 

right side window post number 3, and 

in the window upper sill structure. 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 165 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per product Cost on U.S. operators 

Inspections ................. Up to 193 work-hours × $85 per 

hour = $16,405 per inspection 

cycle.

$0 Up to $16,405 per inspection 

cycle.

Up to $2,706,825 per inspection 

cycle. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

specified in this AD. 

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 

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 


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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 

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): 

2016–16–10 The Boeing Company: 

Amendment 39–18608; Docket No. 

FAA–2015–8429; Directorate Identifier 

2015–NM–122–AD. 

(a) Effective Date 

This AD is effective September 14, 2016. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to The Boeing Company 

Model 747–100, 747–100B, 747–100B SUD, 

747–200B, 747–200C, 747–200F, 747–300, 

747–400, 747–400D, 747–400F, 747SR, and 

747SP series airplanes, certificated in any 

category, as identified in Boeing Alert 

Service Bulletin 747–53A2862, Revision 1, 

dated July 24, 2015. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by reports of 

fatigue cracks in the station 320 crown frame 

in window post number 3. We are issuing 

this AD to detect and correct fatigue cracking 

and missing fasteners of the station 320 

crown frame, cracking of the window post 

number 3, and cracking of the window upper 

sill, which could result in an in-flight 

decompression and a loss of structural 

integrity of the fuselage. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Initial Inspections, Related Investigative 

Actions, and Corrective Actions 

At the applicable time specified in 

paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Alert Service Bulletin 747–53A2862, 

Revision 1, dated July 24, 2015, except as 

provided by paragraphs (j)(1) and (j)(2) of this 

AD: Do the actions specified in paragraphs 

(g)(1) through (g)(5) of this AD; and do all 

applicable related investigative and 

corrective actions; in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2862, Revision 1, 

dated July 24, 2015, except as required by 

paragraph (j)(3) of this AD. Do all applicable 

related investigative and corrective actions 

before further flight. 

(1) Do a detailed inspection for cracks and 

missing fasteners of the station 320 crown 

frame. 

(2) Do a surface high frequency eddy 

current (HFEC) inspection for cracks of the 

station 320 crown frame. 

(3) Do a surface HFEC inspection for cracks 

in the web and flange surfaces of the forward 

segment of window post number 3. 

(4) Do a detailed inspection for missing 

fasteners of the window upper sill. 

(5) Do a surface HFEC inspection for cracks 

of the window upper sill. 

(h) Repetitive Inspections and Post-Repair 

Inspections, Related Investigative Actions, 

and Corrective Actions 

Do applicable repetitive post-repair 

inspections and repeat the inspections 

specified in paragraphs (g)(1) through (g)(5) 

of this AD thereafter at the applicable 

compliance time and intervals specified in 

paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Alert Service Bulletin 747–53A2862, 

Revision 1, dated July 24, 2015; and do all 

applicable related investigative and 

corrective actions; in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2862, Revision 1, 

dated July 24, 2015, except as required by 

paragraph (j)(3) of this AD. Do all applicable 

related investigative and corrective actions 

before further flight. 

(i) Fastener Rework, Related Investigative 

Actions, and Corrective Actions 

At the applicable time specified in 

paragraph 1.E., ‘‘Compliance,’’ of Boeing 

Alert Service Bulletin 747–53A2862, 

Revision 1, dated July 24, 2015: Do the 

applicable actions (including fastener rework 

and a detailed inspection of the condition of 

the fastener hole) specified in Part 11 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2862, Revision 1, 

dated July 24, 2015; and do all applicable 

related investigative and corrective actions; 

in accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–53A2862, Revision 1, dated July 24, 

2015, except as specified in paragraph (j)(3) 

of this AD. Do all applicable related 

investigative and corrective actions before 

further flight. 

(j) Exceptions to Service Information 

Specifications 

(1) Where Boeing Alert Service Bulletin 

747–53A2862, Revision 1, dated July 24, 

2015, specifies a compliance time ‘‘after the 

original date of this service bulletin,’’ this AD 

requires compliance within the specified 

compliance time after the effective date of 

this AD. 

(2) Where Boeing Alert Service Bulletin 

747–53A2862, Revision 1, dated July 24, 

2015, specifies a compliance time ‘‘after the 

Revision 1 date of this service bulletin,’’ this 

AD requires compliance within the specified 

compliance time after the effective date of 

this AD. 

(3) Where Boeing Alert Service Bulletin 

747–53A2862, Revision 1, dated July 24, 

2015, specifies to contact Boeing for repairs: 

Before further flight, repair, using a method 

approved in accordance with the procedures 

specified in paragraph (k)(1) of this AD. 

(k) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in 

paragraph (l)(1) of this AD. Information may 

be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/

certificate holding district office. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair, 

modification, or alteration required by this 

AD if it is approved the Boeing Commercial 

Airplanes Organization Designation 

Authorization (ODA) that has been 

authorized by the Manager, Seattle ACO, to 

make those findings. To be approved, the 

repair method, modification deviation, or 

alteration deviation must meet the 

certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(4) Except as required by paragraphs (g), 

(h), and (j)(3) of this AD: For service 

information that contains steps that are 

labeled as Required for Compliance (RC), the 

provisions of paragraphs (k)(4)(i) and 

(k)(4)(ii) apply. 

(i) The steps labeled as RC, including 

substeps under an RC step and any figures 

identified in an RC step, must be done to 

comply with the AD. An AMOC is required 

for any deviations to RC steps, including 

substeps and identified figures. 

(ii) Steps not labeled as RC may be 

deviated from using accepted methods in 

accordance with the operator’s maintenance 

or inspection program without obtaining 

approval of an AMOC, provided the RC steps, 


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52758 Federal Register / Vol. 81, No. 154 / Wednesday, August 10, 2016 / Rules and Regulations 

including substeps and identified figures, can 

still be done as specified, and the airplane 

can be put back in an airworthy condition. 

(l) Related Information 

For more information about this AD, 

contact Bill Ashforth, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

ACO, 1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: 425–917–6432; fax: 425– 

917–6590; email: Bill.Ashforth@faa.gov. 

(m) 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 the AD specifies otherwise. 

(i) Boeing Alert Service Bulletin 747– 

53A2862, Revision 1, dated July 24, 2015. 

(ii) Reserved. 

(3) For Boeing service information 

identified in this AD, 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. 

(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 July 27, 

2016. 

Victor Wicklund, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–18487 Filed 8–9–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–8468; Directorate 

Identifier 2014–NM–208–AD; Amendment 

39–18605; AD 2016–16–07] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2007–21– 

14 R1 for all Airbus Model A310 series 

airplanes. AD 2007–21–14 R1 required 

revising the Airworthiness Limitations 

Section of the Instructions for 

Continued Airworthiness to incorporate 

new limitations for fuel tank systems. 

This new AD requires revising the 

maintenance program or inspection 

program to incorporate revised fuel 

maintenance and inspection tasks. This 

AD was prompted by the issuance of 

more restrictive maintenance 

requirements and/or airworthiness 

limitations by the manufacturer. We are 

issuing this AD to prevent the potential 

of ignition sources inside fuel tanks, 

which, in combination with flammable 

fuel vapors caused by latent failures, 

alterations, repairs, or maintenance 

actions, could result in fuel tank 

explosions and consequent loss of the 

airplane. 

DATES: This AD becomes effective 

September 14, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of September 14, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

this AD as of November 20, 2007 (72 FR 

58499, October 16, 2007). 

ADDRESSES: For service information 

identified in this final rule, contact 

Airbus SAS, Airworthiness Office— 

EAW, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone 

+33 5 61 93 36 96; fax +33 5 61 93 44 

51; email account.airworth-eas@

airbus.com; Internet http://

www.airbus.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 

Number FAA–2015–8468. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket Number FAA– 

2015–8468; 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 Operations office (telephone 

800–647–5527) is in the ADDRESSES

section. 

FOR FURTHER INFORMATION CONTACT: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–2125; 

fax 425–227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2007–21–14 R1, 

Amendment 39–16061 (74 FR 55123, 

October 27, 2009) (‘‘AD 2007–21–14 

R1’’). AD 2007–21–14 R1 applied to all 

Airbus Model A310 series airplanes. 

The NPRM published in the Federal 

Register on January 20, 2016 (81 FR 

3066) (‘‘the NPRM’’). The NPRM was 

prompted by the issuance of more 

restrictive maintenance requirements 

and/or airworthiness limitations by the 

manufacturer. The NPRM proposed to 

retain the requirements of AD 2007–21– 

14 R1, and require more restrictive 

maintenance requirements and/or 

airworthiness limitations. We are 

issuing this AD to prevent the potential 

of ignition sources inside fuel tanks, 

which, in combination with flammable 

fuel vapors caused by latent failures, 

alterations, repairs, or maintenance 

actions, could result in fuel tank 

explosions and consequent loss 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 2014–0193, dated October 15, 

2014 (referred to after this as the 

Mandatory Continuing Airworthiness 

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

an unsafe condition on all Airbus Model 

A310 series airplanes. The MCAI states: 

Prompted by an accident * * *, the 

Federal Aviation Administration (FAA) 

published Special Federal Aviation 

Regulation (SFAR) 88, and the Joint Aviation 

Authorities (JAA) published Interim Policy 

INT/POL/25/12. In response to these 

regulations, Airbus conducted a design 

review to develop Fuel Airworthiness 

Limitations (FAL) for Airbus on A310 

aeroplanes. 

The FAL were specified in Airbus A310 

FAL document ref. 95A.1930/05 at issue 02 

and in the A310 Airworthiness Limitations 

Section (ALS) variation to FAL document 

issue 02, ref. 0BVLG110006/C0S issue 01, for 

A310 aeroplanes. 

EASA issued [EASA] AD 2006–0202 to 

require compliance with the FAL documents 

(comprising maintenance/inspection tasks 

and Critical Design Configuration Control 

Limitations (CDCCL)). 

EASA AD 2006–0202 was superseded by 

EASA AD 2007–0096 (later revised) [which 

corresponds to FAA AD 2007–21–14 R1], 

which retained the original requirements and 


Lhorne on DSK30JT082PROD with RULES