Federal Register / Vol. 81, No. 69 / Monday, April 11, 2016 / Rules and Regulations 21263 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends part 39 of the Federal 

Aviation Regulations (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) 

2015–20–13, Amendment 39–18292 (80 

FR 61725, October 14, 2015) and adding 

the following new AD: 

2016–07–21 Piper Aircraft, Inc.: 

Amendment 39–18466; Docket No. 

FAA–2016–5432; Directorate Identifier 

2016–CE–009–AD. 

(a) Effective Date 

This AD is effective April 26, 2016. 

(b) Affected ADs 

This AD replaces AD 2015–20–13, 

Amendment 39–18292 (80 FR 61725) (‘‘AD 

2015–20–13’’). 

(c) Applicability 

This AD applies to the following Piper 

Aircraft, Inc. airplanes certificated in any 

category. 

(1) Airplanes previously affected by AD 

2015–20–13: Model PA–28–161 airplanes, 

serial numbers (S/Ns) 2842393 through 

2842395; Model PA–28–181 airplanes, S/Ns 

2843769 through 2843775 and 2843779 

through 2843791; and Model PA–28R–201 

airplanes, S/N 2844152. 

(2) Airplanes new to this AD: Model PA– 

28–161 airplanes, S/Ns 2842010 through 

2842392; Model PA–28–181 airplanes, S/Ns 

2843021 through 2843768; and Model PA– 

28R–201 airplane, S/Ns 2844004 through 

2844151. 

(d) Subject 

Joint Aircraft System Component (JASC)/

Air Transport Association (ATA) of America 

Code 5712, Wing Ribs/Bulkhead. 

(e) Unsafe Condition 

This AD was prompted by reports of cracks 

found in the wing rib on airplanes outside 

the Applicability, paragraph (c), of AD 2015– 

20–13. The cracks occurred in production 

during forming of the wing rib bead radius. 

We are issuing this AD to detect and correct 

cracks in the wing rib, which if not corrected, 

could result in reduced structural integrity of 

the wing with consequent loss of control. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspect 

(1) Inspect the right wing rib at wing 

station (WS) 140.09 for cracks at the 

following compliance times. 

(i) For airplanes previously affected by AD 

2015–20–13: Within the next 25 hours timein-service after (TIS) after October 29, 2015 

(the effective date retained from AD 2015– 

20–13) following the INSTRUCTIONS section 

of Piper Aircraft, Inc. Service Bulletin No. 

1279, dated August 26, 2015, or Piper 

Aircraft, Inc. Service Bulletin No. 1279A, 

dated March 3, 2016. 

(ii) For airplanes new to this AD: Within 

the next 25 hours TIS after April 26, 2016 

(the effective date of this AD) following the 

INSTRUCTIONS section of Piper Aircraft, 

Inc. Service Bulletin No. 1279A, dated March 

3, 2016. 

(2) If any crack is detected during the 

inspection required by paragraph (g)(1) of 

this AD, before further flight, obtain and 

implement an FAA-approved repair scheme, 

approved specifically for this AD. At the 

operator’s discretion, assistance may be 

provided by contacting Piper Aircraft, Inc. at 

the address identified in paragraph (k)(5) of 

this AD. 

(h) Special Flight Permit 

A special flight permit is allowed for this 

AD per 14 CFR 39.23 for the inspection 

required in paragraph (g)(1) of this AD. If a 

crack is found during the inspection required 

in paragraph (g)(1) of this AD, a special flight 

permit is allowed with the following 

limitations: 

(1) Flight must be planned to the nearest 

location where repairs can be done; 

(2) Indicated airspeed must be 120 knots or 

less for the entire flight; 

(3) Bank angle is not to exceed 30 degrees 

for the entire flight; 

(4) Maximum load factors must be between 

+3.0 and ¥1.0 for the entire flight; and 

(5) Flight must be performed VFR, with no 

turbulence greater than ‘‘light’’ forecast for 

the planned flight route and altitude. 

(i) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Atlanta 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 (j) of this AD. 

(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. 

(j) Related Information 

For more information about this AD, 

contact Gregory ‘‘Keith’’ Noles, Aerospace 

Engineer, FAA, Atlanta ACO, 1701 Columbia 

Avenue, College Park, Georgia 30337; phone: 

(404) 474–5551; fax: (404) 474–5606; email: 

gregory.noles@faa.gov. 

(k) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

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

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(3) The following service information was 

approved for IBR on April 26, 2016. 

(i) Piper Aircraft, Inc. Service Bulletin No. 

1279A, dated March 3, 2016. 

(ii) Reserved. 

(4) The following service information was 

approved for IBR on October 29, 2015 (80 FR 

61725, October 14, 2015). 

(i) Piper Aircraft, Inc. Service Bulletin No. 

1279, dated August 26, 2015. 

(ii) Reserved. 

(5) For Piper Aircraft, Inc. service 

information identified in this AD, contact 

Piper Aircraft, Inc., Customer Service, 2926 

Piper Drive, Vero Beach, Florida 32960; 

telephone: (877) 879–0275; fax: none; email: 

customer.service@piper.com; Internet: 

www.piper.com. 

(6) You may review the referenced service 

information at the FAA, Small Airplane 

Directorate, 901 Locust, Kansas City, 

Missouri 64106. For information on the 

availability of this material at the FAA, call 

(816) 329–4148. It is also available on the 

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

searching for locating Docket No. FAA–2016– 

5432. 

(7) 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 Kansas City, Missouri, on March 

28, 2016. 

Jacqueline Jambor, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2016–07580 Filed 4–8–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–1279; Directorate 

Identifier 2014–NM–049–AD; Amendment 

39–18454; AD 2016–07–09] 

RIN 2120–AA64 

Airworthiness Directives; BAE 

SYSTEMS (Operations) Limited 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 


jstallworth on DSK7TPTVN1PROD with RULES
21264 Federal Register / Vol. 81, No. 69 / Monday, April 11, 2016 / Rules and Regulations 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2011–21– 

06 for all BAE SYSTEMS (Operations) 

Limited Model 4101 airplanes. AD 

2011–21–06 required revising the 

maintenance program. This new AD 

requires a new revision of the 

maintenance or inspection program. 

This AD was prompted by a 

determination that the life limit of 

certain main landing gear components 

must be reduced, and certain post-repair 

inspections of critical structure are 

necessary. We are issuing this AD to 

prevent failure of certain structurally 

significant items, including the main 

landing gear and nose landing gear, 

which could result in reduced structural 

integrity of the airplane; and to prevent 

fuel vapor ignition sources, which could 

result in a fuel tank explosion and 

consequent loss of the airplane. 

DATES: This AD is effective May 16, 

2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of May 16, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

this AD as of November 23, 2011 (76 FR 

64788, October 19, 2011). 

ADDRESSES: For service information 

identified in this final rule, 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. It is also 

available on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

1279. 

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– 

1279; 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: 

Theodore (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: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2011–21–06, 

Amendment 39–16829 (76 FR 64788, 

October 19, 2011) (‘‘AD 2011–21–06’’). 

AD 2011–21–06 applied to all BAE 

SYSTEMS (Operations) Limited Model 

4101 airplanes. The NPRM published in 

the Federal Register on May 8, 2015 (80 

FR 26484) (‘‘the NPRM’’). 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2014–0043, dated February 21, 

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 

4101 airplanes. The MCAI states: 

The Jetstream J41 Aircraft Maintenance 

Manual (AMM), includes the following 

chapters: 

05–10–10 ‘‘Airworthiness Limitations’’, 

05–10–20 ‘‘Certification Maintenance 

Requirements’’, and, 

05–10–30 ‘‘Critical Design Configuration 

Control Limitations (CDCCL)—Fuel 

System’’. 

The maintenance tasks and limitations 

contained in these chapters have been 

identified as mandatory actions for continued 

airworthiness and EASA issued AD 2010– 

0098 [dated May 27, 2010 (http://

ad.easa.europa.eu/ad/2010-0098) which 

corresponds to FAA AD 2011–21–06, 

Amendment 39–16829 (79 FR 64788, October 

19, 2011)] to require operators to comply 

with those instructions. 

Since that [EASA] AD was issued, BAE 

Systems (Operations) Ltd issued Revision 37 

of the AMM amending Chapter 05–10–10 to 

revise and reduce the life limit of certain 

main landing gear components. In addition, 

Revision 38 of the AMM was issued to 

amend Chapters 05–10–00 and 05–10–10 

introducing inspections to be accomplished 

after implementation of some repairs 

affecting fatigue strength of critical structure. 

Failure to comply with the new and more 

restrictive actions could result in an unsafe 

condition. 

For the reasons described above, this 

[EASA] AD, which supersedes EASA AD 

2010–0098, requires implementation of the 

maintenance requirements and/or 

airworthiness limitations as specified in the 

defined parts of Chapter 05 of the AMM at 

Revision 38. 

The unsafe condition is the failure of 

certain structurally significant items, 

including the main landing gear and 

nose landing gear, which could result in 

reduced structural integrity of the 

airplane; and fuel vapor ignition 

sources, which could result in a fuel 

tank explosion 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 Docket No. 

FAA–2015–1279. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM or 

on the determination of the cost to the 

public. 

Explanation of Change to NPRM 

Since we issued the NPRM, we 

discovered an incorrect reference to 

‘‘paragraph (j)’’ in paragraph (i)(3) of the 

proposed AD. The correct reference is to 

‘‘paragraph (i),’’ and we have changed 

this AD accordingly. 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting this AD 

with the change described previously 

and for minor editorial changes. We 

have determined that these 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 Subjects 05–10–10, 

‘‘Airworthiness Limitations’’; 05–10–20, 

‘‘Certification Maintenance 

Requirements’’; and 05–10–30, ‘‘Critical 

Design Configuration Control 

Limitations (CDCCL)—Fuel System’’; of 

Chapter 05, ‘‘Airworthiness 

Limitations,’’ of the BAE Systems 

(Operations) Limited J41 AMM, 

Revision 38, dated September 15, 2013. 

This service information describes 

procedures for inspections of 

structurally significant items and the 

fuel system. 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. 


jstallworth on DSK7TPTVN1PROD with RULES
Federal Register / Vol. 81, No. 69 / Monday, April 11, 2016 / Rules and Regulations 21265 

Costs of Compliance 

We estimate that this AD affects 4 

airplanes of U.S. registry. 

The actions required by AD 2011–21– 

06, Amendment 39–16829 (76 FR 

64788, October 19, 2011), and retained 

in this AD take about 1 work-hour per 

product, at an average labor rate of $85 

per work-hour. Based on these figures, 

the estimated cost of the actions that are 

required by AD 2011–21–06 is $85 per 

product. 

We also estimate that it would take 

about 1 work-hour per product to 

comply with the basic requirements of 

this AD. The average labor rate is $85 

per work-hour. Based on these figures, 

we estimate the cost of this AD on U.S. 

operators to be $340, 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 AD will not 

have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

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

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); 

3. Will not affect intrastate aviation in 

Alaska; and 

4. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by 

removing Airworthiness Directive (AD) 

2011–21–06, Amendment 39–16829 (76 

FR 64788, October 19, 2011), and 

adding the following new AD: 

2016–07–09 BAE SYSTEMS (Operations) 

Limited: Amendment 39–18454. Docket 

No. FAA–2015–1279; Directorate 

Identifier 2014–NM–049–AD. 

(a) Effective Date 

This AD is effective May 16, 2016. 

(b) Affected ADs 

This AD replaces AD 2011–21–06, 

Amendment 39–16829 (76 FR 64788, October 

19, 2011) (‘‘AD 2011–21–06’’). 

(c) Applicability 

This AD applies to all BAE SYSTEMS 

(Operations) Limited Model 4101 airplanes, 

certificated in any category. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 05. 

(e) Reason 

This AD was prompted by the need to 

reduce the life limit of certain main landing 

gear components, and to add certain postrepair inspections of critical structure to the 

maintenance or inspection program. We are 

issuing this AD to prevent failure of certain 

structurally significant items, including the 

main landing gear and nose landing gear, 

which could result in reduced structural 

integrity of the airplane; and to prevent fuel 

vapor ignition sources, which could result in 

a fuel tank explosion and consequent loss of 

the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Maintenance Program Revision, 

With No Changes 

This paragraph restates the requirements of 

paragraph (i) of AD 2011–21–06, with no 

changes. Within 90 days after November 23, 

2011 (the effective date of AD 2011–21–06): 

Revise the maintenance program by 

incorporating Subjects 05–10–10, 

‘‘Airworthiness Limitations’’; 05–10–20, 

‘‘Certification Maintenance Requirements’’; 

and 05–10–30, ‘‘Critical Design Configuration 

Control Limitations (CDCCL)—Fuel System’’; 

of Chapter 05, ‘‘Airworthiness Limitations,’’ 

of the BAE Systems (Operations) Limited 

Jetstream Series 4100 Aircraft Maintenance 

Manual (AMM), Revision 35, dated February 

15, 2011. The initial compliance times for the 

tasks are at the applicable times specified in 

paragraphs (g)(1), (g)(2), and (g)(3) of this AD. 

Doing the actions required by paragraph (i) 

of this AD terminates the requirements of this 

paragraph. 

(1) For replacement tasks of life limited 

parts specified in Subject 05–10–10, 

‘‘Airworthiness Limitations,’’ of Chapter 05, 

‘‘Airworthiness Limitations,’’ of the BAE 

Systems (Operations) Limited Jetstream 

Series 4100 AMM, Revision 35, dated 

February 15, 2011: Prior to the applicable 

flight cycles (landings) or flight hours (flying 

hours) on the part specified in the 

‘‘Mandatory Life Limits’’ column in Subject 

05–10–10, or within 90 days after November 

23, 2011 (the effective date of AD 2011–21– 

06), whichever occurs later. 

(2) For structurally significant item tasks 

specified in Subject 05–10–10, 

‘‘Airworthiness Limitations,’’ of Chapter 05, 

‘‘Airworthiness Limitations,’’ of the BAE 

Systems (Operations) Limited Jetstream 

Series 4100 AMM, Revision 35, dated 

February 15, 2011: Prior to the accumulation 

of the applicable flight cycles specified in the 

‘‘Initial Inspection’’ column in Subject 05– 

10–10, or within 90 days after November 23, 

2011 (the effective date of AD 2011–21–06), 

whichever occurs later. 

(3) For certification maintenance 

requirements tasks specified in Subject 05– 

10–20, ‘‘Certification Maintenance 

Requirements,’’ of Chapter 05, 

‘‘Airworthiness Limitations,’’ of the BAE 

Systems (Operations) Limited Jetstream 

Series 4100 AMM, Revision 35, dated 

February 15, 2011: Prior to the accumulation 

of the applicable flight hours specified in the 

‘‘Time Between Checks’’ column in Subject 

05–10–20, or within 90 days after November 

23, 2011 (the effective date of AD 2011–21– 

06), whichever occurs later; except for tasks 

that specify ‘‘first flight of the day’’ in the 

‘‘Time Between Checks’’ column in Subject 

05–10–20, the initial compliance time is the 

first flight of the next day after doing the 

revision required by paragraph (g) of this AD, 

or within 90 days after November 23, 2011 

(the effective date of AD 2011–21–06), 

whichever occurs later. 

(h) Retained Restrictions on Alternative 

Actions, Intervals, and/or CDCCLs, With a 

New Exception 

This paragraph restates the requirements of 

paragraph (k) of AD 2011–21–06, with a new 

exception. Except as required by 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 (l) of this 

AD. 


jstallworth on DSK7TPTVN1PROD with RULES
21266 Federal Register / Vol. 81, No. 69 / Monday, April 11, 2016 / Rules and Regulations 

(i) New Maintenance or Inspection Program 

Revision 

Within 90 days after the effective date of 

this AD: Revise the maintenance or 

inspection program, as applicable, by 

incorporating Subjects 05–10–10, 

‘‘Airworthiness Limitations’’; 05–10–20, 

‘‘Certification Maintenance Requirements’’; 

and 05–10–30, ‘‘Critical Design Configuration 

Control Limitations (CDCCL)—Fuel System’’; 

of Chapter 05, ‘‘Airworthiness Limitations,’’ 

of the BAE Systems (Operations) Limited J41 

AMM, Revision 38, dated September 15, 

2013. The initial compliance times for the 

tasks are at the applicable times specified in 

paragraphs (i)(1), (i)(2), and (i)(3) of this AD. 

Doing the actions required by this paragraph 

terminates the requirements of paragraph (g) 

of this AD. 

(1) For replacement tasks of life limited 

parts specified in Subject 05–10–10, 

‘‘Airworthiness Limitations,’’ of Chapter 05, 

‘‘Airworthiness Limitations,’’ of the BAE 

Systems (Operations) Limited J41 AMM, 

Revision 38, dated September 15, 2013: Prior 

to the applicable flight cycles (landings) or 

flight hours (flying hours) on the part 

specified in the ‘‘Mandatory Life Limits’’ 

column in Subject 05–10–10, or within 90 

days after the effective date of this AD, 

whichever occurs later. 

(2) For structurally significant item tasks 

specified in Subject 05–10–10, 

‘‘Airworthiness Limitations,’’ of Chapter 05, 

‘‘Airworthiness Limitations,’’ of the BAE 

Systems (Operations) Limited J41 AMM, 

Revision 38, dated September 15, 2013: Prior 

to the accumulation of the applicable flight 

cycles specified in the ‘‘Initial Inspection’’ 

column in Subject 05–10–10, or within 90 

days after the effective date of this AD, 

whichever occurs later. 

(3) For certification maintenance 

requirements tasks specified in Subject 05– 

10–20, ‘‘Certification Maintenance 

Requirements,’’ of Chapter 05, 

‘‘Airworthiness Limitations,’’ of the BAE 

Systems (Operations) Limited J41 AMM, 

Revision 38, dated September 15, 2013: Prior 

to the accumulation of the applicable flight 

hours specified in the ‘‘Time Between 

Checks’’ column in Subject 05–10–20, or 

within 90 days after the effective date of this 

AD, whichever occurs later; except for tasks 

that specify ‘‘first flight of the day’’ in the 

‘‘Time Between Checks’’ column in Subject 

05–10–20, the initial compliance time is the 

first flight of the next day after doing the 

revision required by paragraph (i) of this AD, 

or within 90 days the effective date of this 

AD, whichever occurs later. 

(j) New Restrictions on Alternative Actions, 

Intervals, and/or (CDCCLs) 

After the maintenance or inspection 

program, as applicable, has been revised as 

required by paragraph (i) 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 AMOC in accordance with 

the procedures specified in paragraph (l) of 

this AD. 

(k) Credit for Previous Actions 

This paragraph restates the provisions of 

paragraph (j) of AD 2011–21–06. This 

paragraph provides credit for actions 

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

actions were performed before November 23, 

2011 (the effective date of AD 2011–21–06), 

in accordance with Subjects 05–10–10, 

‘‘Airworthiness Limitations’’; 05–10–20, 

‘‘Certification Maintenance Requirements’’; 

and 05–10–30, ‘‘Critical Design Configuration 

Control Limitations (CDCCL)—Fuel System’’; 

of Chapter 05, ‘‘Airworthiness Limitations,’’ 

of the BAE Systems (Operations) Limited 

Jetstream Series 4100 AMM, Revision 33, 

dated February 15, 2010; which are not 

incorporated by reference in this AD. 

(l) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(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: 

Theodore (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. 

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

AMOC-REQUESTS@faa.gov. 

(i) 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. 

(ii) AMOCs approved previously for AD 

2011–21–06, are not approved as AMOCs 

with this AD. 

(2) Contacting the Manufacturer: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer, the action must 

be accomplished using a method approved 

by the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

the 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 DOAauthorized signature. 

(m) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2014–0043, dated 

February 21, 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–2015–1279. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (n)(5) and (n)(6) of this AD. 

(n) 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. 

(3) The following service information was 

approved for IBR on May 16, 2016. 

(i) Chapter 05, ‘‘Airworthiness 

Limitations,’’ of the BAE Systems 

(Operations) Limited J41 Aircraft 

Maintenance Manual (AMM), Revision 38, 

dated September 15, 2013. Page 1 of the 

‘‘Publications Transmittal’’ is the only page 

that shows the revision level of this 

document. 

(A) Subject 05–10–10, ‘‘Airworthiness 

Limitations.’’ 

(B) Subject 05–10–20, ‘‘Certification 

Maintenance Requirements.’’ 

(C) Subject 05–10–30, ‘‘Critical Design 

Configuration Control Limitations (CDCCL)— 

Fuel System.’’ 

(ii) Reserved. 

(4) The following service information was 

approved for IBR on November 23, 2011 (76 

FR 64788, October 19, 2011). 

(i) Chapter 05, ‘‘Airworthiness 

Limitations,’’ of the BAE Systems 

(Operations) Limited Jetstream Series 4100 

AMM, Revision 35, dated February 15, 2011. 

Page 1 of the Publications Transmittal of the 

BAE Systems (Operations) Limited Jetstream 

Series 4100 AMM is the only page that shows 

the revision level of this document. 

(A) Subject 05–10–10, ‘‘Airworthiness 

Limitations.’’ 

(B) Subject 05–10–20, ‘‘Certification 

Maintenance Requirements.’’ 

(C) Subject 05–10–30, ‘‘Critical Design 

Configuration Control Limitations (CDCCL)— 

Fuel System.’’ 

(ii) Reserved. 

(5) 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. 

(6) 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. 

(7) 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 March 

22, 2016. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–07229 Filed 4–8–16; 8:45 am] 

BILLING CODE 4910–13–P 


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