Federal Register / Vol. 81, No. 117 / Friday, June 17, 2016 / Rules and Regulations 39547 

(2) Repeat the borescope inspection 

required by this AD every 300 hours since 

last inspection. 

(3) If any crack, loss of contact between the 

ferrule and diffuser axial vane, or any contact 

between the injection manifold supply pipe 

and the diffuser ferrule is found, remove the 

diffuser case and replace the ferrule with a 

part eligible for installation. 

(f) Credit for Previous Actions 

You may take credit for the actions 

required by paragraph (e) of this AD if you 

performed those actions using Turbomeca 

S.A. MSB No. 298 72 2832, Version B, dated 

October 12, 2015 or earlier versions, before 

the effective date of this AD. 

(g) Alternative Methods of Compliance 

(AMOCs) 

The Manager, Engine Certification Office, 

FAA, may approve AMOCs for this AD. Use 

the procedures found in 14 CFR 39.19 to 

make your request. You may email your 

request to: ANE-AD-AMOC@faa.gov. 

(h) Related Information 

(1) For more information about this AD, 

contact Brian Kierstead, Aerospace Engineer, 

Engine Certification Office, FAA, Engine & 

Propeller Directorate, 1200 District Avenue, 

Burlington, MA 01803; phone: 781–238– 

7772; fax: 781–238–7199; email: 

brian.kierstead@faa.gov. 

(2) Refer to MCAI European Aviation 

Safety Agency AD 2015–0209R1, dated April 

20, 2016, for more information. You may 

examine the MCAI in the AD docket on the 

Internet at http://www.regulations.gov by 

searching for and locating it in Docket No. 

FAA–2015–8257. 

(i) 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) Turbomeca S.A. Alert MSB No. A298 72 

2832, Version C, dated April 15, 2016. 

(ii) Reserved. 

(3) For Turbomeca S.A. service information 

identified in this AD, contact Turbomeca 

S.A., 40220 Tarnos, France; phone: (33) 05 59 

74 40 00; fax: (33) 05 59 74 45 15. 

(4) You may view this service information 

at FAA, Engine & Propeller Directorate, 1200 

District Avenue, Burlington, MA. For 

information on the availability of this 

material at the FAA, call 781–238–7125. 

(5) You may view this service information 

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 Burlington, Massachusetts, on 

June 10, 2016. 

Colleen M. D’Alessandro, 

Manager, Engine & Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. 2016–14234 Filed 6–16–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0027; Directorate 

Identifier 2010–NM–127–AD; Amendment 

39–18543; AD 2016–11–16] 

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 777–200 

and -300 series airplanes equipped with 

Rolls-Royce Model RB211-Trent 800 

engines. This AD was prompted by 

reports of thrust reverser (T/R) events 

related to thermal damage of the T/R 

inner wall. Depending on the airplane 

configuration, this AD requires a records 

review and applicable repetitive 

inspections, replacements, and 

installations of the T/R inner wall; and 

related investigative and corrective 

actions if necessary. This AD also 

requires installation of serviceable T/R 

halves, which would terminate the 

repetitive actions. This AD also requires 

revising the inspection or maintenance 

program by incorporating new 

airworthiness limitations. We are 

issuing this AD to detect and correct a 

degraded T/R inner wall panel. A 

degraded T/R inner wall panel could 

lead to failure of the T/R and adjacent 

components and their consequent 

separation from the airplane, which 

could result in a rejected takeoff (RTO) 

and cause asymmetric thrust and 

consequent loss of control of the 

airplane during reverse thrust operation. 

If a T/R inner wall overheats, separated 

components could cause structural 

damage to the airplane, damage to other 

airplanes, or possible injury to people 

on the ground. 

DATES: This AD is effective July 22, 

2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of July 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–2011– 

0027. 

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–2011– 

0027; 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: 

Kevin Nguyen, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, 

Seattle Aircraft Certification Office 

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

WA 98057–3356; phone: 425–917–6501; 

fax: 425–917–6590; email: 

kevin.nguyen@faa.gov. 

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 The Boeing 

Company Model 777–200 and -300 

series airplanes equipped with RollsRoyce Model RB211-Trent 800 engines. 

The SNPRM published in the Federal 

Register on September 25, 2015 (80 FR 

57744) (‘‘the SNPRM’’). We preceded 

the SNPRM with a notice of proposed 

rulemaking (NPRM) that published in 

the Federal Register on January 20, 

2011 (76 FR 3561) (‘‘the NPRM’’). The 

NPRM proposed to require repetitive 

inspections for degradation of T/R 

structure and sealant, and related 

investigative and corrective actions if 


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necessary. The NPRM was prompted by 

reports of T/R events related to thermal 

damage of the T/R inner wall. The 

SNPRM proposed to revise the NPRM 

by adding different repetitive inspection 

requirements for T/R halves with a 

thermal protective system installed. The 

SNPRM also proposed to revise the 

NPRM by requiring installation of 

serviceable T/R halves, which would 

terminate the repetitive inspections. The 

SNPRM also proposed to revise the 

inspection or maintenance program by 

incorporating new airworthiness 

limitations. We are issuing this AD to 

detect and correct a degraded T/R inner 

wall panel. A degraded T/R inner wall 

panel could lead to failure of the T/R 

and adjacent components and their 

consequent separation from the 

airplane, which could result in an RTO 

and cause asymmetric thrust and 

consequent loss of control of the 

airplane during reverse thrust operation. 

If a T/R inner wall overheats, separated 

components could cause structural 

damage to the airplane, damage to other 

airplanes, or possible injury to people 

on the ground. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the SNPRM and the FAA’s 

response to each comment. 

Request To Change Compliance 

Reference 

Boeing requested that we revise 

paragraph (k)(2) of the proposed AD (in 

the SNPRM) by adding ‘‘table 5’’ to the 

reference to the Compliance paragraph 

in Boeing Service Bulletin 777–78– 

0082, Revision 1, dated June 15, 2015. 

Boeing stated that this change would be 

consistent with how paragraph (k)(1) of 

the proposed AD (in the SNPRM) refers 

to the Compliance paragraph. 

We agree with the commenter’s 

request for the reason provided. We 

have revised paragraph (k)(2) of this AD 

accordingly. 

Request To Modify Alternative Method 

of Compliance (AMOC) Statement 

Boeing requested that the AMOC 

statement specified in paragraph (r)(3) 

of the proposed AD (in the SNPRM) be 

revised by adding a sentence to allow an 

AMOC for the serviceable T/R assembly 

to be transferred to other airplanes. 

Boeing stated that an AMOC provided 

for a repaired and serviceable unit is 

able to be attached to and travel with 

the repaired unit. Boeing added that a 

serviceable unit is a rotable part and can 

be installed on multiple airplanes 

during the life of the unit. Boeing noted 

that paragraph (l)(3) of AD 2015–19–16, 

Amendment 39–18278 (80 FR 59570, 

October 2, 2015) contains language 

similar to the requested language. 

We disagree with the request because 

we are now able to issue an AMOC that 

applies to multiple products operated 

by a single operator (commonly referred 

to as a fleet AMOC). This procedure 

allows AMOCs to address rotable parts. 

We have not changed this AD in this 

regard. 

Request To Update Service Information 

Boeing requested that the revision 

date of Boeing 777 Maintenance 

Planning Data (MPD) Document Section 

9, Airworthiness Limitations (AWLs) 

and Certification Maintenance 

Requirements (CMRs), D622W001–9, 

Revision dated October 2014, be 

updated to reflect the latest FAAapproved revision. Boeing stated that 

AWL 78–AWL–01, Thrust Reverser 

Thermal Protection System, was revised 

recently to include Boeing Alert Service 

Bulletin 777–78A0094, dated July 29, 

2014, in the applicability note of the 

AWL. 

We agree to reference the most recent 

revision of Boeing 777 MPD Document 

Section 9, AWLs and CMRs, 

D622W001–9 (which is referred to as 

Temporary Revision (TR) 09–030, 

Revision dated November 2015, on 

MyBoeingFleet.com), because the new 

applicability note clarifies that AWL 

78–AWL–01 applies to T/R halves on 

which the actions specified in Boeing 

Alert Service Bulletin 777–78A0094 

have been done. As a result, we have 

revised the introductory text to 

paragraph (n) of this AD accordingly. 

We have also added a new paragraph 

(p)(5) to this AD to provide credit for 

accomplishing the revision required by 

paragraph (n) of this AD using Boeing 

777 MPD Document, Section 9, AWLs 

and CMRs, D622W001–9, Revision 

dated October 2014. 

Request To Modify Initial Inspection 

Boeing requested that paragraph (n)(1) 

of the proposed AD (in the SNPRM) be 

revised to allow deferral of the initial 

inspection for AWL 78–AWL–01, Thrust 

Reverser Thermal Protection System. 

Boeing stated that the compliance time 

should be 1,125 days or 6,000 flight 

cycles, whichever occurs first, after the 

last inspection for AWL 78–AWL–01, 

Thrust Reverser Thermal Protection 

System, ‘‘for T/Rs that have already 

incorporated 78–AWL–01.’’ Boeing 

stated that when the AD becomes 

effective, T/R halves on which Boeing 

Alert Service Bulletin 777–78A0094 and 

AWL 78–AWL–01, Thrust Reverser 

Thermal Protection System, have been 

incorporated are not subject to the 

inspections specified in paragraph (i) of 

the proposed AD (in the SNPRM) and 

should not be required to do the 

inspection required by AWL 78–AWL– 

01 concurrent with the next inspection 

required by paragraph (i) of this AD or 

within 30 days after the effective date of 

this AD, whichever occurs later. 

We agree with allowing deferral of the 

initial inspection for AWL 78–AWL–01, 

Thrust Reverser Thermal Protection 

System, for the reasons provided by the 

commenter. We have revised the 

compliance time for AWL 78–AWL–01, 

Thrust Reverser Thermal Protection 

System, as requested by the commenter. 

We have revised the introductory text to 

paragraph (n), and reformatted and 

revised paragraphs (n)(1) and (n)(2) of 

this AD, to accommodate the 

commenter’s request. We clarified the 

affected airplanes for the compliance as 

specified in paragraph (n)(1) of this AD 

by stating, ‘‘For airplanes on which any 

inspections required by paragraph (i) of 

this AD are done.’’ We clarified the 

affected airplanes for the compliance as 

specified in paragraph (n)(2) of this AD 

by stating, ‘‘For airplanes on which the 

installation required by paragraph (l) of 

this AD is done.’’ 

Request To Review Inspection Methods 

American Airlines requested that the 

FAA review the inspection methods and 

instructions required in paragraph (i) of 

the proposed AD (in the SNPRM) when 

doing a nondestructive test (NDT) 

inspection for delaminations and 

disbonds; and ensuring false positive 

findings are prevented or minimized. 

American Airlines stated that they 

inspected eight T/R inner walls in 

accordance with paragraph (i)(1) of the 

proposed AD (in the SNPRM) and found 

disbonded material. American Airlines 

stated that after they contacted the 

original equipment manufacturer (OEM) 

and re-inspected, several units were 

determined to be false positives. 

American Airlines surmised that the 

instructions or possible training for 

inspections may not be sufficient. 

We acknowledge the commenter’s 

concern. However, we have determined 

the NDT inspections for disbonds and 

damage required in paragraph (i) and 

associated service information produce 

reliable inspection results and 

adequately detect disbonds and damage. 

Through technical discussion with the 

OEM, we understand that the false 

positive indications were a result of a 

maintenance vendor using a non-OEM 

inspection manual that had a faulty 

NDT inspection standard. We have not 

revised this AD in this regard. 


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Request To Review Airworthiness 

Limitation Inspection Procedures 

American Airlines stated it had a T/ 

R inner wall that required repair, but the 

damage would not have been detected 

by the inspection specified in 

Airworthiness Limitation 78–AWL–02, 

Thrust Reverser Inner Wall, as specified 

in Boeing MPD Document, Section 9, 

AWLs and CMRs, D622W001–9, 

Revision dated October 2014. American 

Airlines stated the damage would likely 

have passed inspection because it did 

not indicate any heat discoloration, and 

other areas of disbonds or damage on 

the inner wall could be potentially 

missed after the incorporation of Boeing 

Alert Service Bulletin 777–78A0094, 

dated July 29, 2014, and AWL 78–AWL– 

02. We infer the commenter is 

requesting that we review AWL 78– 

AWL–02 to ensure that thermal damage 

on the inner wall is not missed. 

We acknowledge the commenter’s 

concern, and we might consider 

additional rulemaking to address that 

concern in the future. We contacted 

Boeing, and Boeing stated they are 

working with American Airlines to 

determine if a change needs to be made 

to the service information. However, 

until such additional action is 

identified, we consider it appropriate to 

proceed with issuance of this final rule 

to address the identified unsafe 

condition. We have not changed this 

final rule in this regard. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting this AD 

with the changes described previously 

and 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. 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of this AD. 

Related Service Information Under 1 

CFR Part 51 

We reviewed the following Boeing 

service information. 

• Boeing Alert Service Bulletin 777– 

78A0065, Revision 2, dated May 6, 

2010. This service information describes 

procedures for a review of the airplane 

maintenance records to determine 

whether sealant was added to insulation 

blankets around compression pad 

fittings and the powered door opening 

system (PDOS) fitting; inspections of the 

T/R structure; and related investigative 

and corrective actions. 

• Boeing Alert Service Bulletin 777– 

78A0094, dated July 29, 2014. This 

service information describes 

procedures for installing serviceable 

T/R halves. 

• Boeing Service Bulletin 777–78– 

0082, Revision 1, dated June 15, 2015; 

and Boeing Special Attention Service 

Bulletin 777–78–0071, Revision 2, dated 

July 23, 2013. This service information 

describes, among other actions, 

procedures for inspections of the T/R 

structure, and related investigative and 

corrective actions, if necessary. Boeing 

Special Attention Service Bulletin 777– 

78–0071, Revision 2, dated July 23, 

2013, also describes, for airplanes on 

which the actions specified in Boeing 

Special Attention Service Bulletin 777– 

78–0071, dated November 29, 2009, 

have been done, procedures for 

installation of click bond covers and a 

bracket, a general visual inspection of 

the compression fitting for incorrect pin 

orientation, and related investigative 

and corrective actions, if necessary. 

• Boeing 777 Maintenance Planning 

Data (MPD) Document, Section 9, 

Airworthiness Limitations (AWLs) and 

Certification Maintenance Requirements 

(CMRs), D622W001 9, Revision dated 

November 2015. This service 

information provides required AWLs 

and CMRs for The Boeing Company 

Model 777 airplanes. The two AWLs 

specifically required by this AD are 

AWL 78–AWL–01, Thrust Reverser 

Thermal Protection System, which 

describes an inspection of the T/R 

thermal protection system on both 

engines; and AWL 78 AWL–02, which 

describes an inspection of the T/R inner 

wall. 

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 55 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 

ESTIMATED COSTS

Action Work hours 

Average 

labor rate 

per hour 

Parts cost Cost per product Fleet cost 

Actions per Boeing Alert Service 

Bulletin 777-78A0065, Revision 

2, dated May 6, 2010.

Up to 79 workhours, per T/R 

half.

$85 $0 ...................... Up to $6,715 per 

T/R half.

$0 (No airplanes on the U.S. 

Register are in the configuration specified in Boeing Alert 

Service Bulletin 777-78A0065, 

Revision 2, dated May 6, 

2010.) 

Actions per Boeing Special Attention Service Bulletin 

777-78-0071, Revision 2, dated 

July 23, 2013.

Up to 48 workhours, per T/R 

half.

85 $0 ...................... Up to $4,080 per 

T/R half.

Up to $897,600 (4 T/R halves per 

airplane). 

Inspections per Boeing Service 

Bulletin 777-78-0082, Revision 

1, dated June 15, 2015.

Up to 39 workhours, per T/R 

half.

85 $0 ...................... Up to $3,315 per 

T/R half.

$0 (No airplanes on the U.S. 

Register are in the configuration specified in Boeing Service 

Bulletin 777-78-0082, Revision 

1, dated June 15, 2015.) 

Maintenance or Inspection Program Revision.1 work-hour ....... 85 $0 ...................... $85 .................... $4,675. 


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ESTIMATED COSTS—Continued 

Action Work hours 

Average 

labor rate 

per hour 

Parts cost Cost per product Fleet cost 

T/R half installation per Boeing 

Alert Service Bulletin 

777-78A0094, dated July 29, 

2014.

Up to 206 workhours, per T/R 

half.

85 Up to $400,651 

per T/R half 1.

Up to $418,161 

per T/R half.

Up to $91,995,420 (4 T/R halves 

per airplane).2

1The cost of parts is split into two major parts: (1) Thermal protection system (TPS) blankets and (2) inner wall structure. The vast majority of 

the work associated with the TPS upgrade has already been completed. In addition, nearly half of the inner wall structure modification has already been done. 2The fleet cost estimate above is based on a general estimate for a given airplane with two engines having two T/R halves for each engine. 

Not all tasks required by this AD and specified in the service information would need to be done for a given T/R half. For a given TR half, it may 

only be necessary to accomplish certain actions or none for compliance, depending on its configuration status. We have no data to determine 

any given T/R half configuration to determine the cost for each T/R half to do the applicable actions for that T/R half. The majority of this cost 

has already been incurred. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

specified in this AD. 

According to the manufacturer, some 

of the costs of this AD may be covered 

under warranty, thereby reducing the 

cost impact on affected individuals. We 

do not control warranty coverage for 

affected individuals. As a result, we 

have included all costs in our cost 

estimate. 

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 

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): 

2016–11–16 The Boeing Company: 

Amendment 39–18543; Docket No. 

FAA–2011–0027; Directorate Identifier 

2010–NM–127–AD. 

(a) Effective Date 

This AD is effective July 22, 2016. 

(b) Affected ADs 

This AD affects AD 2005–07–24, 

Amendment 39–14049 (70 FR 18285, April 

11, 2005). 

(c) Applicability 

This AD applies to The Boeing Company 

Model 777–200 and –300 series airplanes, 

certificated in any category, equipped with 

Rolls-Royce Model RB211-Trent 800 engines. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 78, Engine exhaust. 

(e) Unsafe Condition 

This AD was prompted by reports of thrust 

reverser (T/R) events related to thermal 

damage of the T/R inner wall. We are issuing 

this AD to detect and correct a degraded 

T/R inner wall panel. A degraded T/R inner 

wall panel could lead to failure of the T/R 

and adjacent components and their 

consequent separation from the airplane, 

which could result in a rejected takeoff (RTO) 

and cause asymmetric thrust and consequent 

loss of control of the airplane during reverse 

thrust operation. If a T/R inner wall 

overheats, separated components could cause 

structural damage to the airplane, damage to 

other airplanes, or possible injury to people 

on the ground. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Records Review, Inspections, and Related 

Investigative and Corrective Actions for 

Airplanes With Pre-Thermal Protection 

System (TPS) Insulation Blankets (Part 

Numbers (P/Ns) 315W5113–(XX) and 

315W5010–(XX)) Installed 

For airplanes with pre-TPS insulation 

blankets, P/Ns 315W5113–(XX) and 

315W5010–(XX): Except as required by 

paragraphs (h)(1), (h)(2), (h)(3), and (h)(4) of 

this AD, at the applicable time in paragraph 

1.E., ‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 777–78A0065, Revision 2, dated 

May 6, 2010, review the airplane 

maintenance records to determine whether 

sealant was added to insulation blankets 

around the compression pad fittings and the 

powered door opening system (PDOS) fitting; 

do the applicable actions specified in 

paragraphs (g)(1), (g)(2), (g)(3), (g)(4), (g)(5), 

and (g)(6) of this AD; and do all applicable 

related investigative and corrective actions; 

in accordance with the applicable work 

packages of the Accomplishment Instructions 

of Boeing Alert Service Bulletin 777– 

78A0065, Revision 2, dated May 6, 2010, 

except as required by paragraph (h)(5) of this 

AD. Do all applicable related investigative 

and corrective actions before further flight. 


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Repeat the applicable inspections, 

replacement, and installations required by 

paragraphs (g)(1), (g)(2), (g)(3), (g)(4), (g)(5), 

and (g)(6) of this AD thereafter at the 

applicable intervals specified in paragraph 

1.E., ‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 777–78A0065, Revision 2, dated 

May 6, 2010. 

(1) Do a detailed inspection of all T/R inner 

wall insulation blanket edges, grommet 

holes, penetrations, and seams for sealant 

that is cracked, has gaps, is loose, or is 

missing; do a general visual inspection of 

click bond studs, blanket studs, and 

temporary fasteners; and replace sealant as 

applicable. 

(2) Do the actions specified by either 

paragraph (g)(2)(i) or (g)(2)(ii) of this AD. 

(i) Do a full inner wall panel 

nondestructive test (NDT) inspection for 

delamination and disbonding of each T/R 

half, and do a general visual inspection for 

areas of thermal degradation. 

(ii) Do a limited area NDT inspection of the 

inner wall panel of each T/R half for 

delamination and disbonding, and do a 

general visual inspection for areas of thermal 

degradation. 

(3) Do a general visual inspection of the T/ 

R perforated wall aft of the intermediate 

pressure compressor 8th stage (IP8) and the 

high pressure compressor 3rd stage (HP3) 

bleed port exits for a color that is different 

from that of the general area. 

(4) Do a detailed inspection of the PDOS 

lug bushings on the upper number 1 

compression pad fittings to detect hole 

elongation, deformation, and contact with the 

PDOS actuator; and install a PDOS actuator 

rod and sealant. 

(5) Do an NDT inspection for unsatisfactory 

number 1 upper and numbers 1 and 2 lower 

compression pad fittings. 

(6) Install and seal insulation blankets. 

(h) Exceptions to Specifications of Boeing 

Alert Service Bulletin 777–78A0065, 

Revision 2, Dated May 6, 2010 

(1) Where paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Alert Service Bulletin 777–78A0065, 

Revision 2, dated May 6, 2010, specifies a 

compliance time ‘‘after the date on the 

original issue of this service bulletin,’’ this 

AD requires compliance within the specified 

compliance time after the effective date of 

this AD. 

(2) Where table 2 of paragraph 1.E., 

‘‘Compliance,’’ in Boeing Alert Service 

Bulletin 777–78A0065, Revision 2, dated 

May 6, 2010, specifies a compliance time of 

‘‘2,000 flight cycles after the date of the 

operator’s own inspections,’’ for doing Work 

Packages 2 and 5, or Work Packages 5 and 

6, this AD requires compliance within 2,000 

flight cycles after the date of the operator’s 

own inspections, or within 12 months after 

the effective date of this AD, whichever 

occurs later. 

(3) Where the Condition column in table 2 

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

Alert Service Bulletin 777–78A0065, 

Revision 2, dated May 6, 2010, refers to a T/ 

R half that has or has not been inspected 

before ‘‘the date on this service bulletin,’’ this 

AD requires compliance for each 

corresponding T/R half that has or has not 

been inspected before the effective date of 

this AD. 

(4) Where the Condition column in tables 

2 and 3 of paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Alert Service Bulletin 777–78A0065, 

Revision 2, dated May 6, 2010, refers to ‘‘total 

flight cycles,’’ this AD applies to each T/R 

half with the specified total flight cycles as 

of the effective date of this AD. 

(5) Where Boeing Alert Service Bulletin 

777–78A0065, Revision 2, dated May 6, 2010, 

specifies to contact Boeing for appropriate 

action: Before further flight, repair using a 

method approved in accordance with the 

procedures specified in paragraph (r) of this 

AD. 

(i) Repetitive NDT and Additional 

Inspections for Airplanes With TPS 

Insulation Blankets (P/N 315W5115–(XX)) 

Installed 

For airplanes with TPS insulation blankets, 

P/N 315W5115–(XX): Within 2,000 flight 

cycles after doing any NDT inspection 

specified in Boeing Special Attention Service 

Bulletin 777–78–0071; or within 2,000 flight 

cycles after doing any NDT inspection 

specified in Boeing Service Bulletin 777–78– 

0082; or within 30 days after the effective 

date of this AD; whichever occurs latest; do 

the inspections specified in paragraphs (i)(1) 

and (i)(2) of this AD, and do all applicable 

related investigative and corrective actions, 

in accordance with the Accomplishment 

Instructions of Boeing Special Attention 

Service Bulletin 777–78–0071, Revision 2, 

dated July 23, 2013, or in accordance with 

the Accomplishment Instructions of Boeing 

Service Bulletin 777–78–0082, Revision 1, 

dated June 15, 2015, as applicable; except as 

required by paragraph (m) of this AD. Do all 

applicable related investigative and 

corrective actions before further flight. 

Repeat the inspections specified in 

paragraphs (i)(1) and (i)(2) of this AD 

thereafter at the applicable time specified in 

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

Special Attention Service Bulletin 777–78– 

0071, Revision 2, dated July 23, 2013; or 

Boeing Service Bulletin 777–78–0082, 

Revision 1, dated June 15, 2015; as 

applicable. 

(1) Do an NDT inspection of the full T/R 

inner wall panel for delaminations and 

disbonds. 

(2) Do a detailed inspection of the 

perforated side of the T/R inner wall aft of 

the IP8 and the HP3 bleed port exits for color 

that is different from the normal T/R 

perforated wall color. 

(j) Concurrent Requirements for Paragraph 

(i) of This AD 

For airplanes with TPS insulation blankets, 

P/N 315W5115–(XX), on which any action 

specified in Boeing Special Attention Service 

Bulletin 777–78–0071 have been done but 

the actions specified in paragraphs (j)(1) and 

(j)(2) of this AD have not been done: Prior to 

or concurrently with doing the inspection 

required by paragraph (i) of this AD, do the 

actions specified in paragraphs (j)(1) and 

(j)(2) of this AD, in accordance with the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 777–78– 

0071, Revision 2, dated July 23, 2013, except 

as required by paragraph (m) of this AD. 

(1) Install click bond covers and bracket 

and replace the washers. 

(2) Do a detailed inspection of the 

compression fitting for incorrect pin 

orientation, and do all applicable related 

investigative and corrective actions. Do all 

applicable related investigative and 

corrective actions before further flight. 

(k) Repetitive Electronic Engine Control 

(EEC) Wire Bundle Inspections for Airplanes 

With TPS Insulation Blankets (P/N 

315W5115–(XX)) Installed 

For airplanes with TPS insulation blankets, 

P/N 315W5115–(XX): Do the inspections 

specified in paragraphs (k)(1) or (k)(2) of this 

AD, as applicable. 

(1) For airplanes on which any inspection 

specified in Boeing Special Attention Service 

Bulletin 777–78–0071 has been done: Within 

2,000 flight hours after doing a detailed 

inspection of the EEC wire bundles and clips 

as specified in Boeing Special Attention 

Service Bulletin 777–78–0071, or within 500 

flight hours after the effective date of this AD, 

whichever occurs later; do a detailed 

inspection of the EEC wire bundles and clips 

for damage, and do all applicable corrective 

actions, in accordance with the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 777–78– 

0071, Revision 2, dated July 23, 2013, except 

as required by paragraph (m) of this AD. Do 

all applicable corrective actions before 

further flight. Repeat the inspection 

thereafter at the applicable time specified in 

table 5 of paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Special Attention Service Bulletin 

777–78–0071, Revision 2, dated July 23, 

2013. 

(2) For airplanes on which any inspection 

specified in Boeing Service Bulletin 777–78– 

0082, has been done: Within 2,000 flight 

hours after doing a detailed inspection of the 

EEC wire bundles and clips as specified in 

Boeing Special Attention Service Bulletin 

777–78–0082, or within 500 flight hours after 

the effective date of this AD, whichever 

occurs later; do a detailed inspection for 

damage of the EEC wire bundles and clips, 

and do all applicable corrective actions, in 

accordance with the Accomplishment 

Instructions of Boeing Service Bulletin 777– 

78–0082, Revision 1, dated June 15, 2015, 

except as required by paragraph (m) of this 

AD. Do all applicable corrective actions 

before further flight. Repeat the inspection 

thereafter at the applicable time specified in 

table 5 of paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Service Bulletin 777–78–0082, 

Revision 1, dated June 15, 2015. 

(l) T/R Inner Wall Installation 

Within 48 months after the effective date 

of this AD: Install serviceable T/R halves, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

777–78A0094, dated July 29, 2014, except as 

required by paragraph (m) of this AD. The 

definition of a serviceable T/R half is 

specified in Boeing Alert Service Bulletin 

777–78A0094, dated July 29, 2014. 

Accomplishing the installation specified in 

this paragraph and the revision to the 

maintenance or inspection program required 

by paragraph (n) of this AD terminates the 


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39552 Federal Register / Vol. 81, No. 117 / Friday, June 17, 2016 / Rules and Regulations 

actions required by paragraphs (g), (i), (j), and 

(k) of this AD. 

(m) Exceptions to Service Information 

Specified in Paragraphs (i), (j), (k), and (l) of 

This AD 

Where Boeing Alert Service Bulletin 777– 

78A0094, dated July 29, 2014; Boeing Service 

Bulletin 777–78–0082, Revision 1, dated June 

15, 2015; and Boeing Special Attention 

Service Bulletin 777–78–0071, Revision 2, 

dated July 23, 2013; specify to contact Boeing 

for appropriate action: Before further flight, 

repair using a method approved in 

accordance with the procedures specified in 

paragraph (r) of this AD. 

(n) Revise the Maintenance or Inspection 

Program 

Within 30 days after the effective date of 

this AD, revise the maintenance or inspection 

program, as applicable, to incorporate 

Airworthiness Limitations 78–AWL–01, 

Thrust Reverser Thermal Protection System; 

and 78–AWL–02, Thrust Reverser Inner Wall; 

as specified in Boeing 777 Maintenance 

Planning Data (MPD) Document, Section 9, 

Airworthiness Limitations (AWLs) and 

Certification Maintenance Requirements 

(CMRs), D622W001–9, Revision dated 

November 2015. The initial compliance times 

for AWLs 78–AWL–01, Thrust Reverser 

Thermal Protection System, and 78–AWL– 

02, Thrust Reverser Inner Wall, as specified 

in Boeing 777 MPD Document, Section 9, 

AWLs and CMRs, D622W001–9, Revision 

dated November 2015, are at the applicable 

time specified in paragraph (n)(1) or (n)(2) of 

this AD. 

(1) For airplanes on which any inspections 

required by paragraph (i) of this AD are done: 

Concurrent with the next inspection required 

by paragraph (i) of this AD, or within 30 days 

after the effective date of this AD, whichever 

occurs later. 

(2) For airplanes on which the installation 

required by paragraph (l) of this AD is done: 

At the later of the times specified in 

paragraph (n)(2)(i) and (n)(2)(ii) of this AD. 

(i) Within 1,125 days or 6,000 flight cycles, 

whichever occurs first after accomplishing 

the installation required by paragraph (l) of 

this AD. 

(ii) Within 30 days after the effective date 

of this AD. 

(o) No Alternative Actions or Intervals 

After the maintenance or inspection 

program, as applicable, has been revised as 

required by paragraph (n) of this AD, no 

alternative actions (e.g., inspections) or 

intervals may be used unless the actions or 

intervals are approved as an alternative 

method of compliance (AMOC) in 

accordance with the procedures specified in 

paragraph (r) of this AD. 

(p) Credit for Previous Actions 

(1) This paragraph provides credit for the 

actions specified in paragraph (g) of this AD, 

if those actions were performed before the 

effective date of this AD using Boeing Alert 

Service Bulletin 777–78A0065, dated June 

23, 2008; or Boeing Alert Service Bulletin 

777–78A0065, Revision 1, dated January 29, 

2009. This service information is not 

incorporated by reference in this AD. 

(2) This paragraph provides credit for the 

actions specified in paragraph (i) of this AD, 

if those actions were performed before the 

effective date of this AD using any service 

information specified in paragraphs (p)(2)(i), 

(p)(2)(ii), and (p)(2)(iii) of this AD. This 

service information is not incorporated by 

reference in this AD. 

(i) Boeing Service Bulletin 777–78–0082, 

dated November 9, 2011. 

(ii) Boeing Special Attention Service 

Bulletin 777–78–0071, dated November 25, 

2009. 

(iii) Boeing Special Attention Service 

Bulletin 777–78–0071, Revision 1, dated 

September 8, 2010. 

(3) This paragraph provides credit for the 

actions specified in paragraph (j) of this AD, 

if those actions were performed before the 

effective date of this AD using Boeing Special 

Attention Service Bulletin 777–78–0071, 

Revision 1, dated September 8, 2010. This 

service information is not incorporated by 

reference in this AD. 

(4) This paragraph provides credit for the 

actions specified in paragraph (k)(2) of this 

AD, if those actions were performed before 

the effective date of this AD using Boeing 

Service Bulletin 777–78–0082, dated 

November 9, 2011. This service information 

is not incorporated by reference in this AD. 

(5) This paragraph provides credit for the 

actions specified in paragraph (n) of this AD, 

if those actions were performed before the 

effective date of this AD using Boeing 777 

MPD Document, Section 9, AWLs and CMRs, 

D622W001–9, Revision dated October 2014. 

This service information is not incorporated 

by reference in this AD. 

(q) Terminating Action for AD 2005–07–24, 

Amendment 39–14049 (70 FR 18285, April 

11, 2005) 

Accomplishing the actions specified in 

paragraph (q)(1), (q)(2), or (q)(3) of this AD 

terminates the actions required by paragraphs 

(f), (g), and (h) of AD 2005–07–24, 

Amendment 39–14049 (70 FR 18285, April 

11, 2005). 

(1) The actions required by paragraph (g) 

of this AD. 

(2) The inspections required by paragraphs 

(i) and (k) of this AD, and, as applicable, the 

actions required by paragraph (j) of this AD. 

(3) The installation specified in paragraph 

(l) of this AD. 

(r) 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 (s)(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 by 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. 

(s) Related Information 

(1) For more information about this AD, 

contact Kevin Nguyen, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, Seattle 

ACO, 1601 Lind Avenue SW., Renton, 

Washington 98057–3356; phone: 425–917– 

6501; fax: 425–917–6590; email: 

kevin.nguyen@faa.gov. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

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

(t) 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 777– 

78A0065, Revision 2, dated May 6, 2010. 

(ii) Boeing Alert Service Bulletin 777– 

78A0094, dated July 29, 2014. 

(iii) Boeing Service Bulletin 777–78–0082, 

Revision 1, dated June 15, 2015. 

(iv) Boeing Special Attention Service 

Bulletin 777–78–0071, Revision 2, dated July 

23, 2013. 

(v) Boeing 777 Maintenance Planning Data 

(MPD) Document, Section 9, Airworthiness 

Limitations (AWLs) and Certification 

Maintenance Requirements (CMRs), 

D622W001–9, Revision dated November 

2015. 

(3) For 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. 


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Federal Register / Vol. 81, No. 117 / Friday, June 17, 2016 / Rules and Regulations 39553 

Issued in Renton, Washington, on May 20, 

2016. 

Victor Wicklund, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–13051 Filed 6–16–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–8137; Directorate 

Identifier 2014–NM–104–AD; Amendment 

39–18561; AD 2016–12–12] 

RIN 2120–AA64 

Airworthiness Directives; Fokker 

Services B.V. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2008–05– 

18 R1 for certain Fokker Services B.V. 

Model F.27 Mark 050, 200, 300, 400, 

500, 600, and 700 airplanes. AD 2008– 

05–18 R1 required revising the 

Airworthiness Limitations Section 

(ALS) of the Instructions for Continued 

Airworthiness to incorporate new 

limitations for fuel tank systems. This 

new AD requires a new maintenance or 

inspection program revision to 

incorporate the revised Airworthiness 

Limitation Items (ALIs) and critical 

design configuration control limitations 

(CDCCLs). This new AD also adds 

certain airplanes to the applicability. 

This AD was prompted by the issuance 

of revised service information to update 

the Fuel ALIs and CDCCLs that address 

fuel tank system ignition sources. We 

are issuing this AD to prevent the 

potential of ignition sources inside fuel 

tanks, which, in combination with 

flammable fuel vapors, could result in 

fuel tank explosions and consequent 

loss of the airplane. 

DATES: This AD becomes effective July 

22, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of July 22, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of November 23, 2009 (74 FR 57402, 

November 6, 2009). 

ADDRESSES: For service information 

identified in this final rule, contact 

Fokker Services B.V., Technical 

Services Dept., P.O. Box 1357, 2130 EL 

Hoofddorp, the Netherlands; telephone 

+31 (0)88–6280–350; fax +31 (0)88– 

6280–111; email technicalservices@

fokker.com; Internet http://

www.myfokkerfleet.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– 

2015–8137. 

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– 

8137; 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 (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, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–1137; 

fax 425–227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2008–05–18 R1, 

Amendment 39–16083 (74 FR 57402, 

November 6, 2009) (‘‘AD 2008–05–18 

R1’’). AD 2008–05–18 R1 applied to 

certain Model F.27 Mark 050, 200, 300, 

400, 500, 600, and 700 airplanes. The 

NPRM published in the Federal 

Register on January 4, 2016 (81 FR 38) 

(‘‘the NPRM’’). The NPRM was 

prompted by the issuance of revised 

service information to update the Fuel 

ALIs and CDCCLs that address fuel tank 

system ignition sources. The NPRM 

proposed to retain the requirements of 

AD 2008–05–18 R1, and require a new 

maintenance or inspection program 

revision to incorporate the revised ALIs 

and CDCCLs. The NPRM also proposed 

to add certain airplanes to the 

applicability. We are issuing this AD to 

prevent the potential of ignition sources 

inside fuel tanks, which, in combination 

with flammable fuel vapors, 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 2015–0029, dated February 24, 

2015 (referred to after this as the 

Mandatory Continuing Airworthiness 

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

an unsafe condition on all Model F.27 

Mark 050, 200, 300, 400, 500, 600, and 

700 airplanes. The MCAI states: 

* * * [T]he FAA published Special 

Federal Aviation Regulation (SFAR) 88, and 

the Joint Aviation Authorities (JAA) 

published Interim Policy INT/POL/25/12. 

The review conducted by Fokker Services on 

the Fokker F27 design in response to these 

regulations identified a number of Fuel 

Airworthiness Limitation Items (ALI) and 

Critical Design Configuration Control 

Limitations (CDCCL) items to prevent the 

development of unsafe conditions within the 

fuel system. 

To introduce these Fuel ALI and CDCCL 

items, Fokker Services published Service 

Bulletin (SB) F27/28–070. Consequently, 

EASA issued AD 2006–0207, requiring the 

implementation of these Fuel ALI and 

CDCCL items. That [EASA] AD was later 

revised to make reference to SBF27–28– 

070R1 and to specify that the use of later SB 

revisions was acceptable. 

In 2014, Fokker Services issued Revision 2 

of SBF27–28–070 to update the Fuel ALI and 

CDCCL items and to consolidate Fuel ALI 

and CDCCL items contained in a number of 

other SBs. Consequently, EASA issued AD 

2014–0105, superseding AD 2006–0207R1 

and requiring the implementation of the 

updated Fuel ALI and CDCCL items. 

Since that [EASA] AD was issued, Fokker 

Services issued Revision 3 of SBF27–28–070, 

primarily to introduce 2 additional CDCCL 

items. 

For the reason described above, this 

[EASA] AD retains the requirements of EASA 

AD 2014–0105, which is superseded, and 

requires implementation of the updated Fuel 

ALI and CDCCL items. 

More information on this subject can be 

found in Fokker Services All Operators 

Message AOF27.043#05. 

The unsafe condition is the potential 

of ignition sources inside fuel tanks. 

Such ignition sources, in combination 

with flammable fuel vapors, could result 

in fuel tank explosions and consequent 

loss of the airplane. You may examine 

the MCAI in the AD docket on the 

Internet at http://www.regulations.gov 

by searching for and locating it in 

Docket No. FAA–2015–8137. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM or 


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