12044 Federal Register / Vol. 81, No. 45 / Tuesday, March 8, 2016 / Proposed Rules 

the FAA proposes to amend 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): 

The Boeing Company: Docket No. FAA– 

2015–0935; Directorate Identifier 2014– 

NM–243–AD. 

(a) Comments Due Date 

We must receive comments by April 22, 

2016. 

(b) Affected ADs 

This AD affects AD 2011–15–03, 

Amendment 39–16750 (76 FR 41659, July 15, 

2011). 

(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 747–28A2306, dated October 

2, 2014. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 28, Fuel. 

(e) Unsafe Condition 

This AD was prompted by several reports 

of chafing of the wire bundles inside the 

electrical conduit of the forward and aft boost 

pumps of the numbers 1 and 4 main fuel 

tanks due to high vibration. These wire 

bundles can chafe through the wire sleeving 

into the insulation, exposing the wire 

conductors. We are issuing this AD to 

prevent chafing of the wire bundles and 

subsequent arcing between the wiring and 

the electrical conduit creating an ignition 

source in the fuel tanks, which could result 

in a fire and consequent fuel tank explosion. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Replacement 

Within 60 months after the effective date 

of this AD: Replace the wire bundles inside 

the electrical conduit of the forward and aft 

boost pumps of the numbers 1 and 4 main 

fuel tanks with new, improved wire bundles 

inserted into conduit liners, in accordance 

with the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–28A2306, 

dated October 2, 2014. Accomplishing the 

replacement required by this paragraph 

terminates the inspections required by 

paragraphs (g), (h), and (n) of AD 2011–15– 

03, Amendment 39–16750 (76 FR 41659, July 

15, 2011). 

(h) Maintenance or Inspection Program 

Revision 

Within 180 days after the effective date of 

this AD, revise the maintenance or inspection 

program, as applicable, to incorporate critical 

design configuration control limitation 

(CDCCL) Task AWL No. 28–AWL–24, ‘‘Fuel 

Boost Pump Wires In Conduit Installation— 

In Fuel Tank,’’ of Sub-section C.1, ‘‘Fuel 

Tank Ignition Prevention,’’ of Section C., 

‘‘Airworthiness Limitations—Systems,’’ of 

the Boeing 747–100/200/300/SP 

Airworthiness Limitations (AWLs) and 

Certification Maintenance Requirements 

(CMRs) Document D6–13747–CMR, Revision 

June 2014; or CDCCL Task No. AWL No. 28– 

AWL–35, ‘‘Fuel Boost Pump Wires In 

Conduit Installation—In Fuel Tank,’’ of Subsection B.1, ‘‘Fuel System Ignition 

Prevention,’’ of Section B, ‘‘Airworthiness 

Limitations (AWLs)—Systems,’’ of Section 9, 

Airworthiness Limitations (AWLs) and 

Certification Maintenance Requirements 

(CMRs), of Boeing 747–400 Maintenance 

Planning Data (MPD) Document D621U400– 

9, Revision June 2014; as applicable. 

(i) No Alternative Actions, Intervals, and/or 

CDCCLs 

After accomplishing the revision required 

by paragraph (h) of this AD, no alternative 

actions (e.g., inspections), intervals, and/or 

CDCCLs may be used unless the actions, 

intervals, and/or CDCCLs are approved as an 

alternative method of compliance (AMOC) in 

accordance with the procedures specified in 

paragraph (j) of this AD. 

(j) 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 (k)(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. 

(k) Related Information 

(1) For more information about this AD, 

contact Tung Tran, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, Seattle 

ACO, 1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: 425–917–6505; fax: 425– 

917–6590; email: tung.tran@faa.gov. 

(2) 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; phone: 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. 

Issued in Renton, Washington, on February 

18, 2016. 

Dorr M. Anderson, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–04681 Filed 3–7–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2016–4220; Directorate 

Identifier 2015–NM–076–AD] 

RIN 2120–AA64 

Airworthiness Directives; BAE 

Systems (Operations) Limited 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

Airworthiness Directive (AD) 2011–24– 

06, for all BAE Systems (Operations) 

Limited Model Avro 146–RJ series 

airplanes. AD 2011–24–06 currently 

requires revising the maintenance 

program to incorporate life limits for 

certain items, adding new and more 

restrictive inspections to detect fatigue 

cracking in certain structures, and 

adding fuel system critical design 

configuration control limitations 

(CDCCLs) to prevent ignition sources in 

the fuel tanks. AD 2011–24–06 also 

currently requires modifying the main 

fittings of the main landing gear (MLG) 

and revising the maintenance program 

to incorporate new life limits on MLG 

up-locks and door up-locks and other 

MLG components. Since we issued AD 

2011–24–06, we have determined that 

new or revised structural inspection 

requirements are necessary. This 

proposed AD would require revising the 

maintenance or inspection program, as 

applicable, to incorporate new or 

revised structural inspection 

requirements. We are proposing this AD 

to detect and correct fatigue cracking of 


asabaliauskas on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 81, No. 45 / Tuesday, March 8, 2016 / Proposed Rules 12045 

certain structural elements, which could 

adversely affect the structural integrity 

of the airplane. 

DATES: We must receive comments on 

this proposed AD by April 22, 2016. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this NPRM, contact BAE Systems 

(Operations) Limited, Customer 

Information Department, Prestwick 

International Airport, Ayrshire, KA9 

2RW, Scotland, United Kingdom; 

telephone +44 1292 675207; fax +44 

1292 675704; email 

RApublications@baesystems.com; 

Internet http://www.baesystems.com/ 

Businesses/RegionalAircraft/index.htm. 

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. 

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– 

4220; 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 proposed 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. Comments will 

be available in the AD docket shortly 

after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Todd Thompson, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone: 425–227–1175; 

fax: 425–227–1149. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2016–4220; Directorate Identifier 

2015–NM–076–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD based on those comments. 

We will post all comments we 

receive, without change, to http:// 

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

On November 8, 2011, we issued AD 

2011–24–06, Amendment 39–16870 (76 

FR 73477, November 29, 2011) (‘‘AD 

2011–24–06’’). AD 2011–24–06 requires 

actions intended to address an unsafe 

condition on all BAE Systems 

(Operations) Limited Model Avro 146– 

RJ series airplanes. 

Since we issued 2011–24–06, 

Amendment 39–16870 (76 FR 73477, 

November 29, 2011), we have 

determined that new or revised 

structural inspection requirements are 

necessary. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2014–0071, dated March 19, 

2014 (referred to after this as the 

Mandatory Continuing Airworthiness 

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

an unsafe condition for all BAE Systems 

(Operations) Limited Model Avro 146– 

RJ series airplanes. The MCAI states: 

The BAe 146/AVRO 146–RJ Aircraft 

Maintenance Manual (AMM) includes the 

Chapters as listed in Appendix 1 of this 

[EASA] AD. Compliance with these chapters 

has been identified as a mandatory action for 

continued airworthiness and EASA AD 

2012–0004 [http://ad.easa.europa.eu/blob/ 

easa_ad_2012_0004_superseded.pdf/ 

AD_2012-0004_1] was issued to require 

operators to comply with those instructions. 

Since that [EASA] AD was issued, BAE 

Systems (Operations) Ltd revised the AMM 

(Revision 107), introducing a new defined 

life limit for the Fire Bottle Cartridge Firing 

Unit into Chapter 05–10–15. Subsequently, 

Revision 108 of the AMM introduced in 

Chapter 05–20–00 inspection tasks for repairs 

applied to fatigue critical structures and also 

introduced a new Chapter 05–20–07 to 

provide Structural Repair Manual (SRM) 

references for these tasks, applicable to 

repairs accomplished after the publication of 

AMM Revision 108. Finally, AMM Revision 

111 introduced safe life limitations into 

Chapter 05–10–15 for rollers of main landing 

gear and door up-locks. 

Furthermore, Section 6 of the Maintenance 

Review Board Report (MRBR) Document 

MRB 146–01, Issue 2, Revision 18 was 

published (as referenced in Chapter 05–20– 

01 of the AMM) to correct discrepancies in 

inspection tasks for a number of Structurally 

Important Items (SIIs). Grace periods for 

these revised inspection tasks are included in 

BAE Systems (Operations) Ltd Inspection 

Service Bulletin (ISB) ISB.53–237. 

Failure to comply with the new and more 

restrictive tasks and limitations referenced 

above could result in an unsafe condition. 

For the reasons described above, this 

[EASA] AD retains the requirements of EASA 

AD 2012–0004, which is superseded, and 

requires implementation of the maintenance 

tasks and/or airworthiness limitations as 

specified in the defined parts of Chapter 05 

of the AMM at Revision 112. 

The unsafe condition is fatigue 

cracking of certain structural elements, 

which could adversely affect the 

structural integrity 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 Docket No. FAA–2016– 

4220. 

FAA’s Determination and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

This proposed AD would require 

revisions to certain operator 

maintenance documents to include new 

actions (e.g., inspections) and/or Critical 

Design Configuration Control 

Limitations (CDCCLs). Compliance with 

these actions and/or CDCCLs is required 

by 14 CFR 91.403(c). For airplanes that 

have been previously modified, altered, 

or repaired in the areas addressed by 

this proposed AD, the operator may not 

be able to accomplish the actions 

described in the revisions. In this 

situation, to comply with 14 CFR 

91.403(c), the operator must request 

approval for an alternative method of 

compliance according to paragraph 

(k)(1) of this proposed AD. The request 

should include a description of changes 


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12046 Federal Register / Vol. 81, No. 45 / Tuesday, March 8, 2016 / Proposed Rules 

to the required actions that will ensure 

the continued damage tolerance of the 

affected structure. 

Costs of Compliance 

We estimate that this proposed AD 

affects 2 airplanes of U.S. registry. 

The actions required by AD 2011–24– 

06 and retained in this proposed AD 

take about 3 work-hours per product, at 

an average labor rate of $85 per workhour. Based on these figures, the 

estimated cost of the actions that are 

required by AD 2011–24–06 is $255 per 

product. 

We also estimate that it would take 

about 1 work-hour per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $85 per work-hour. Based on 

these figures, we estimate the cost of 

this proposed AD on U.S. operators to 

be $170, or $85 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 proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would 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 this proposed regulation: 

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. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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 

removing Airworthiness Directive (AD) 

2011–24–06, Amendment 39–16870 (76 

FR 73477, November 29, 2011) (‘‘AD 

2011–24–06’’), and adding the following 

new AD: 

BAE Systems (Operations) Limited: Docket 

No. FAA–2016–4220; Directorate 

Identifier 2015–NM–076–AD. 

(a) Comments Due Date 

We must receive comments by April 22, 

2016. 

(b) Affected ADs 

This AD replaces AD 2011–24–06, 

Amendment 39–16870 (76 FR 73477, 

November 29, 2011) (‘‘AD 2011–24–06’’). 

(c) Applicability 

This AD applies to BAE Systems 

(Operations) Limited Model Avro 146– 

RJ70A, 146–RJ85A, and 146–RJ100A 

airplanes, certificated in any category, all 

serial numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 05, Periodic Inspections. 

(e) Reason 

This AD was prompted by a determination 

that new or revised structural inspection 

requirements are necessary. We are issuing 

this AD to detect and correct fatigue cracking 

of certain structural elements, which could 

adversely affect the structural integrity of the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Airworthiness Limitations 

Revisions of the Shock Absorber Assemblies 

This paragraph restates the requirements of 

paragraph (j) of AD 2011–24–06, with no 

changes. Within 90 days after January 3, 2012 

(the effective date of AD 2011–24–06), revise 

the maintenance program, by incorporating 

Subject 05–10–15, ‘‘Aircraft Equipment 

Airworthiness Limitations’’ of Chapter 05, 

‘‘Time Limits/Maintenance Checks,’’ of the 

BAE SYSTEMS (Operations) Limited BAe 

146 Series/Avro 146–RJ Series AMM, 

Revision 104, dated April 15, 2011, to 

remove life limits on shock absorber 

assemblies, but not the individual shock 

absorber components, amend life limits on 

main landing gear (MLG) up-locks and door 

up-locks, and to introduce and amend life 

limits on MLG components. Accomplishing 

the actions required by paragraph (i) of this 

AD terminates the actions required by this 

paragraph. 

(h) Retained No Alternative Actions, 

Intervals, and/or Critical Design 

Configuration Control Limitations (CDCCLs), 

With No Changes 

This paragraph restates the requirements of 

paragraph (k) of AD 2011–24–06, with no 

changes. Except as specified in paragraph (i) 

of this AD: After accomplishing the revision 

required by paragraph (g) of this AD, no 

alternative actions (e.g., inspections), 

intervals, and/or CDCCLs may be used, 

unless the actions, intervals, and/or CDCCLs 

are approved as an alternative method of 

compliance (AMOC) in accordance with the 

procedures specified in paragraph (k)(1) of 

this AD. 

(i) New Requirement of this AD: Revise 

Maintenance Program or Inspection 

Program 

Within 90 days after the effective date of 

this AD: Revise the maintenance or 

inspection program, as applicable to 

incorporate new and revised limitations, 

tasks, thresholds, and intervals using a 

method approved by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA. Accomplishing 

the actions required by this paragraph 

terminates the actions required by paragraph 

(g) of this AD. 

Note 1 to paragraph (i) of this AD: An 

additional source of guidance for the actions 

specified in paragraph (i) of this AD can be 

found in BAe 146/AVRO 146–RJ Airplane 

Maintenance Manual, Revision 112, dated 

October 15, 2013. 

Note 2 to paragraph (i) of this AD: An 

additional source of guidance for the actions 

specified in paragraph (i) of this AD can be 

found in Corrosion Prevention Control 

Program (CPCP) Document No. CPCP–146– 

01, Revision 4, dated September 15, 2010. 

Note 3 to paragraph (i) of this AD: An 

additional source of guidance for the actions 

specified in paragraph (i) of this AD can be 

found in Supplemental Structural 

Inspections Document (SSID) Document No. 

SSID–146–01, Revision 2, dated August 15, 

2012. 

Note 4 to paragraph (i) of this AD: An 

additional source of guidance for the actions 

specified in paragraph (i) of this AD can be 

found in Maintenance Review Board Report 

Document No. MRB 146–01, Issue 2, 

Revision 19, dated August 2012. 


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Federal Register / Vol. 81, No. 45 / Tuesday, March 8, 2016 / Proposed Rules 12047 

Note 5 to paragraph (i) of this AD: An 

additional source of guidance for the actions 

specified in paragraph (i) of this AD can be 

found in BAE Systems (Operations) Limited 

Inspection Service Bulletin ISB.53–237, 

Revision 1, dated April 2, 2013. 

(j) New Requirement of This AD: No 

Alternative Actions, Intervals, and 

CDCCLs 

After accomplishment of the revision 

required by paragraph (i) of this AD, no 

alternative actions (e.g., inspections), 

intervals, and CDCCLs may be used, 

unless the actions, intervals, and 

CDCCLs are approved as an AMOC in 

accordance with the procedures 

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

(k) Other FAA AD Provisions 

The following provisions also apply 

to this AD: 

(1) Alternative Methods of 

Compliance (AMOCs): The Manager, 

International Branch, ANM–116, 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: Todd Thompson, 

Aerospace Engineer, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, 1601 Lind Avenue 

SW., Renton, Washington 98057–3356; 

telephone: 425–227–1175; fax: 425– 

227–1149. 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. The 

AMOC approval letter must specifically 

reference this AD. 

(2) Contacting the Manufacturer: As 

of the effective date of this AD, 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 European Aviation Safety Agency 

(EASA); or BAE Systems (Operations) 

Limited’s EASA Design Organization 

Approval (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 Airworthiness Directive 2014– 

0071, dated March 19, 2014, 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– 

4220. 

(2) For service information identified 

in this AD, contact BAE Systems 

(Operations) Limited, Customer 

Information Department, Prestwick 

International Airport, Ayrshire, KA9 

2RW, Scotland, United Kingdom; 

telephone +44 1292 675207; fax +44 

1292 675704; email 

RApublications@baesystems.com; 

Internet http://www.baesystems.com/ 

Businesses/RegionalAircraft/index.htm. 

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. 

Issued in Renton, Washington, on February 

29, 2016. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–04932 Filed 3–7–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2016–4221; Directorate 

Identifier 2015–NM–167–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for all The 

Boeing Company Model 767–200 and 

–300 series airplanes. This proposed AD 

was prompted by an evaluation by the 

design approval holder (DAH) 

indicating that the aft pressure bulkhead 

web to pressure chord joint is subject to 

widespread fatigue damage (WFD). This 

proposed AD would require repetitive 

high frequency eddy current (HFEC) 

inspections of the aft pressure bulkhead 

web, at fasteners common to the 

bulkhead web and pressure chord, 

around the entire circumference of the 

pressure chord for any crack, and repair 

of cracks. We are proposing this AD to 

detect and correct cracks in the aft 

pressure bulkhead web. Such cracking 

could result in the loss of structural 

integrity of the airplane. 

DATES: We must receive comments on 

this proposed AD by April 22, 2016. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this NPRM, 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– 

4221. 

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– 

4221; 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 proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Office 

(phone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

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: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 


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