52872 Federal Register / Vol. 78, No. 166 / Tuesday, August 27, 2013 / Proposed Rules 

640000–26 hat section for cracks. Follow 

Procedure 9 under Vertical Stabilizer in the 

‘‘I’’ Check Procedures of Hawker Beechcraft 

Corporation Model 1900/1900C Airliner 

Structural Inspection Manual, Part Number 

98–30937G2, dated May 1, 2013. 

(4) For Model 1900D airplanes: Within 

1,200 hours TIS after the initial inspection 

required in paragraph (g)(1) of this AD or 

within 2 years after the initial inspection 

required in paragraph (g)(1) of this AD, 

whichever occurs first, and repetitively 

thereafter at intervals not to exceed 1,200 

hours TIS or 2 years, whichever occurs first, 

inspect P/N 101–640011–3 and P/N 101– 

640011–4 spar cap angles for cracks. Follow 

Procedure 6.b. under Vertical Stabilizer 

Canted Stabilizer Station (CSS 69.184 

through VSS 91.10) in the ‘‘I’’ Check 

Procedures of Beechcraft Corporation Model 

1900D Airliner Structural Inspection Manual, 

Part Number 129–590000–65E5, dated May 1, 

2013. 

(5) For Model 1900D airplanes: Within 

1,200 hours TIS after the initial inspection 

required in paragraph (g)(1) of this AD or 

within 2 years after the initial inspection 

required in paragraph (g)(1) of this AD, 

whichever occurs first, and repetitively 

thereafter at intervals not to exceed 1,200 

hours TIS or 2 years, whichever occurs first, 

inspect P/N 114–640000–25 and P/N 114– 

640000–26 hat section for cracks. Follow 

Procedure 6.c. under Vertical Stabilizer 

Canted Stabilizer Station (CSS 69.184 

through VSS 91.10) in the ‘‘I’’ Check 

Procedures of Beechcraft Corporation Model 

1900D Airliner Structural Inspection Manual, 

Part Number 129–590000–65E5, dated May 1, 

2013. 

(h) Repair 

If any cracks are found during any of the 

inspections required in paragraph (g) of this 

AD, to include all subparagraphs, before 

further flight, you must contact Beechcraft 

Corporation to obtain repair instructions 

approved by the Wichita Aircraft 

Certification Office (ACO) specifically for 

compliance with this AD and incorporate 

those instructions. You can find contact 

information for Beechcraft Corporation in 

paragraph (k)(1) of this AD. 

(i) Special Flight Permit 

If cracks are found during any of the 

inspections required in paragraph (g) of this 

AD, to include all subparagraphs, the FAA 

may allow a one-time special flight permit to 

a repair facility depending on the cracking 

found. You must contact Beechcraft 

Corporation and provide them with crack 

detail information for them to determine 

residual strength of the airplane before 

applying to the FAA for a special flight 

permit. You can find contact information for 

Beechcraft Corporation in paragraph (k)(1) of 

this AD. 

(j) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Wichita 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 the 

Related Information section 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. 

(k) Related Information 

(1) For more information about this AD, 

contact Paul Chapman, Aerospace Engineer, 

Wichita Aircraft Certification Office, FAA, 

1801 Airport Road, Room 100, Wichita, 

Kansas 67209; phone: (316) 946–4152; fax: 

(316) 946–4107; email: paul.chapman@

faa.gov. 

(2) For service information identified in 

this AD, contact Beechcraft Corporation at 

address: 10511 E. Central, Wichita, Kansas 

67206; phone: (800) 429–5372 or (316) 676– 

3140; Internet: http://www.beechcraft.com/

customer_support/contact_us/. You may 

review copies of 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. 

Issued in Kansas City, Missouri, on August 

20, 2013. 

Earl Lawrence, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. 2013–20853 Filed 8–26–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0702; Directorate 

Identifier 2012–NM–181–AD] 

RIN 2120–AA64 

Airworthiness Directives; 328 Support 

Services GmbH (Type Certificate 

Previously Held by AvCraft Aerospace 

GmbH; Fairchild Dornier GmbH; 

Dornier Luftfahrt GmbH) Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

airworthiness directive (AD) 2008–14– 

16 that applies to certain 328 Support 

Services GmbH (Type Certificate 

Previously Held by AvCraft Aerospace 

GmbH; Fairchild Dornier GmbH; 

Dornier Luftfahrt GmbH) Model 328– 

100 and 328–300 airplanes. AD 2008– 

14–16 currently requires installing 

warning placards on the inside of the 

passenger door and service doors and 

modifying the hinge supports and 

support struts of the passenger doors. 

Since we issued AD 2008–14–16, we 

received reports that certain fasteners, 

which were installed as part of the 

modification, are the wrong length. This 

proposed AD would require replacing 

the fasteners which were installed as 

part of the modification with new 

fasteners of the correct length, adds new 

airplanes, and removes one airplane. We 

are proposing this AD to prevent 

incidents of inadvertent opening and 

possible detachment of a passenger door 

in-flight, resulting in damage to airframe 

and systems and loss of control of the 

airplane. 

DATES: We must receive comments on 

this proposed AD by October 11, 2013. 

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 proposed AD, contact 328 Support 

Services GmbH, Global Support Center, 

P.O. Box 1252, D–82231 Wessling, 

Federal Republic of Germany; telephone 

+49 8153 88111 6666; fax +49 8153 

88111 6565; email gsc.op@

328support.de; Internet http://

www.328support.de. You may review 

copies of the 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; or in person at the 

Docket Operations office 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, 


pmangrum on DSK3VPTVN1PROD with PROPOSALS-1
Federal Register / Vol. 78, No. 166 / Tuesday, August 27, 2013 / Proposed Rules 52873 

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–2013–0702; Directorate Identifier 

2012–NM–181–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 July 17, 2008, we issued AD 2008– 

14–16, Amendment 39–15611 (73 FR 

40955, July 17, 2008). AD 2008–14–16 

required actions intended to address an 

unsafe condition on 328 Support 

Services GmbH (Type Certificate 

Previously Held by AvCraft Aerospace 

GmbH; Fairchild Dornier GmbH; 

Dornier Luftfahrt GmbH) Model 328– 

100 and Model 328–300 airplanes. 

Since we issued AD 2008–14–16, 

Amendment 39–15611 (73 FR 40955, 

July 17, 2008), we received reports that 

certain fasteners which were installed as 

part of the modification are the wrong 

length and need to be replaced. The 

European Aviation Safety Agency 

(EASA), which is the aviation authority 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2012–0183R1, 

dated September 28, 2012 (referred to 

after this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for the specified products. The MCAI 

states: 

At least one incident occurred where, 

immediately after take-off, the passenger door 

of a Dornier 328 aeroplane completely 

opened. The flight crew reportedly had no 

cockpit indication or audible chime prior to 

this event. The aeroplane returned to the 

departure airfield and made an uneventful 

emergency landing. Substantial damage to 

the door, handrails, door hinge arms and 

fuselage skin were found. 

The subsequent investigation could not find 

any deficiency in the design of the main 

cabin door locking mechanism. In addition, 

no technical failure could be determined that 

precipitated the event. The flight data 

recorder showed that the door was closed 

and locked before take-off and opened 

shortly afterwards. Although final proof 

could not be obtained, the most likely way 

in which the door opened was that the door 

handle was inadvertently operated during the 

take-off run. 

In response to the incident, AvCraft (the TC 

holder at the time) developed a placard set 

to warn the occupants against touching the 

door handle, as well as a structural 

modification of the passenger door hinge 

supports described in [Dornier 328 Support 

Services] Service Bulletin (SB) SB–328–52– 

460 and SB–328J–52–213 to make certain 

that the door does not separate from the 

aeroplane when inadvertently opened during 

flight, allowing a safe descent and landing. 

EASA issued AD 2007–0199 to require the 

installation of warning placards and 

modification as detailed in these SB 

instructions. 

Since that AD [2007–0199] was issued, 328 

Support Services GmbH (the current type 

certificate holder) have determined that 

certain fasteners, identified by Part Number 

(P/N) NAS6703U1 and P/N NAS6703U2, 

which were installed as part of the 

modification, have the wrong length and 

must be replaced. 

For the reasons described above, this [EASA] 

AD retains the requirements of EASA AD 

2007–0199, which is superseded, and 

requires replacement of the affected fasteners 

by the ones that have the correct length. 

This [EASA] AD has been revised to correct 

and clarify the actions required by paragraph 

(3). 

This AD also adds new airplanes and 

removes one airplane from the 

applicability of this AD. You may obtain 

further information by examining the 

MCAI in the AD docket. 

Relevant Service Information 

328 Support Services GmbH has 

issued 328 Support Services Service 

Bulletin SB–328–52–460, Revision 2, 

dated March 1, 2012 (for Model 328–100 

airplanes); and Dornier 328 Support 

Services Service Bulletin SB–328J–52– 

213, Revision 1, dated August 17, 2011 

(for Model 328–300 airplanes). The 

actions described in this service 

information are intended to correct the 

unsafe condition identified in the 

MCAI. 

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. 

Costs of Compliance 

We estimate that this proposed AD 

affects 35 airplanes of U.S. registry. 

We estimate the following costs to 

comply with this proposed AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per product 

Cost on U.S. 

operators 

Modify passenger doors [retained actions from AD 

2008–14–16, Amendment 39–15611 (73 FR 

40955, July 17, 2008)].

38 work-hours × $85 per hour = $3230 $11,961 $15,191 $531,685 

Replace fasteners [new proposed action] .............. 25 work-hours × 85 per hour = 2,125 .... 0 2,125 74,375 

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 


pmangrum on DSK3VPTVN1PROD with PROPOSALS-1
52874 Federal Register / Vol. 78, No. 166 / Tuesday, August 27, 2013 / Proposed Rules 

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. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this proposed AD and placed it in the 

AD docket. 

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) 

2008–14–16, Amendment 39–15611 (73 

FR 40955, July 17, 2008), and adding the 

following new AD: 

328 Support Services GmbH (Type 

Certificate Previously Held by AvCraft 

Aerospace GmbH; Fairchild Dornier 

GmbH; Dornier Luftfahrt GmbH): Docket 

No. FAA–2013–0702; Directorate 

Identifier 2012–NM–181–AD. 

(a) Comments Due Date 

We must receive comments by October 11, 

2013. 

(b) Affected ADs 

This AD supersedes AD 2008–14–16, 

Amendment 39–15611 (73 FR 40955, July 17, 

2008). 

(c) Applicability 

This AD applies to 328 Support Services 

GmbH (Type Certificate previously held by 

AvCraft Aerospace GmbH; Fairchild Dornier 

GmbH; Dornier Luftfahrt GmbH) airplanes, 

certificated in any category, identified in 

paragraphs (c)(1) and (c)(2) of this AD. 

(1) Model 328–100 airplanes, serial 

numbers 3005 through 3101 inclusive, 3103, 

3104, 3106, 3109, 3110, 3112, 3113, 3115, 

3117, and 3119. 

(2) Model 328–300 airplanes, all serial 

numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 11, Placards and Markings; 

and Code 52, Doors. 

(e) Reason 

This AD was prompted by reports that 

certain fasteners, which were installed as 

part of a modification, are the wrong length. 

We are issuing this AD to prevent incidents 

of inadvertent opening and possible 

detachment of a passenger door in-flight, 

resulting in damage to airframe and systems 

and loss of control of the airplane. 

(f) Compliance 

You are responsible for having the actions 

required by this AD performed within the 

compliance times specified, unless the 

actions have already been done. 

(g) Retained Installation and Modification 

for Airplanes Identified in AD 2008–14–16, 

Amendment 39–15611 (73 FR 40955, July 17, 

2008) with Revised Service Information 

This paragraph restates the requirements of 

paragraph (f) of AD 2008–14–16, Amendment 

39–15611 (73 FR 40955, July 17, 2008), with 

revised service information. 

(1) For Model 328–100 airplanes, serial 

numbers 3005 through 3098 inclusive, 3100, 

3106, 3109, 3110, 3112, 3113, 3115, 3117, 

and 3119; and Model 328–300 airplanes, 

having serial numbers 3102, 3105, 3108, 

3111, 3114, 3116, 3118, and 3120 through 

3224 inclusive: Within 30 days after August 

21, 2008, the effective date of AD 2008–14– 

16, Amendment 39–15611 (73 FR 40955, July 

17, 2008), install warning placards on the 

inside of the passenger door and service 

doors, in accordance with the 

Accomplishment Instructions of the service 

information specified in paragraph (g)(1)(i) or 

(g)(1)(ii) of this AD, as applicable. 

(i) Dornier [328 Support Services] Service 

Bulletin SB–328–11–454, dated May 3, 2004 

(for Model 328–100 airplanes). 

(ii) Dornier [328 Support Services] Service 

Bulletin SB–328J–11–209, dated May 3, 2004 

(for Model 328–300 airplanes). 

(2) For Model 328–100 airplanes, serial 

numbers 3005 through 3098 inclusive, 3100, 

3106, 3109, 3110, 3112, 3113, 3115, 3117, 

and 3119; and Model 328–300 airplanes, 

having serial numbers 3102, 3105, 3108, 

3111, 3114, 3116, 3118, and 3120 through 

3224 inclusive: Within 12 months after the 

effective date of August 21, 2008, the 

effective date of AD 2008–14–16, 

Amendment 39–15611 (73 FR 0955, July 17, 

2008), modify the hinge supports and 

support struts of the passenger doors, in 

accordance with the Accomplishment 

Instructions of the service information 

specified in paragraphs (g)(2)(i) through 

(g)(2)(iv) of this AD, as applicable. As of the 

effective date of this AD only the service 

information specified in paragraphs (g)(2)(ii) 

or (g)(2)(iv) of this AD, as applicable, may be 

used. 

(i) Dornier [328 Support Services] Service 

Bulletin SB–328–52–460, dated February 4, 

2005 (for Model 328–100 airplanes). 

(ii) Dornier 328 Support Services Service 

Bulletin SB–328–52–460, Revision 2, dated 

March 1, 2012 (for Model 328–100 airplanes). 

(iii) Dornier [328J Support Services] 

Service Bulletin SB–328J–52–213, dated 

February 4, 2005, (for Model 328–300 

airplanes). 

(iv) Dornier 328J Support Services Service 

Bulletin SB–328J–52–213, Revision 1, dated 

August 17, 2011 (for Model 328–300 

airplanes). 

(h) New Installation and Modification for 

Newly Added Airplanes 

For airplanes not identified in paragraph 

(g) of this AD, do the actions required by 

paragraphs (h)(1) and (h)(2) of this AD. 

(1) Within 30 days after the effective date 

of this AD, install warning placards on the 

inside of the passenger door and service 

doors, in accordance with the 

Accomplishment Instructions of Dornier [328 

Support Services] Service Bulletin SB–328– 

11–454, dated May 3, 2004 (for Model 328– 

100 airplanes); or Dornier [328 Support 

Services] Service Bulletin SB–328J–11–209, 

dated May 3, 2004 (for Model 328–300 

airplanes); as applicable. 

(2) Within 12 months after the effective 

date of this AD, modify the hinge supports 

and support struts of the passenger doors, in 

accordance with the Accomplishment 

Instructions of Dornier 328 Support Services 

Service Bulletin SB–328–52–460, Revision 2, 

dated March 1, 2012 (for Model 328–100 

airplanes); or Dornier 328 Support Services 

Service Bulletin SB–328J–52–213, Revision 

1, dated August 17, 2011 (for Model 328–300 

airplanes); as applicable. 

(i) New Replacement of Fasteners for all 

Airplanes 

For airplanes on which 26 part number 

NAS6703U1 fasteners were installed as 

specified in the service information in 

paragraphs (g)(2)(i) and (g)(2)(iii) of this AD: 

Within 6 months after the effective date of 

this AD, replace the 20 affected part number 

NAS6703U1 fasteners with new fasteners 

having part number NAS6703U2, in 

accordance with the Accomplishment 

Instructions of Dornier 328 Support Services 

Service Bulletin SB–328–52–460, Revision 2, 

dated March 1, 2012 (for Model 328–100 

airplanes); or Dornier 328 Support Services 

Service Bulletin SB–328J–52–213, Revision 

1, dated August 17, 2011 (for Model 328–300 

airplanes); as applicable. 

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

328 Support Services Service Bulletin SB– 


pmangrum on DSK3VPTVN1PROD with PROPOSALS-1
Federal Register / Vol. 78, No. 166 / Tuesday, August 27, 2013 / Proposed Rules 52875 

328–52–460, Revision 2, dated March 1, 2012 

and Dornier 328 Support Services Service 

Bulletin SB–328J–52–213, Revision 1, dated 

August 17, 2011, identify 20 of 26 part 

number NAS6703U1 fasteners requiring to be 

replaced due to incorrect length. 

(j) Credit for Previous Actions 

This paragraph provides credit for certain 

actions required by paragraph (g) and (h)(2) 

of this AD, if those actions were performed 

before the effective date of this AD using 328 

Support Services Service Bulletin SB–328– 

52–460, Revision 1, dated August 17, 2011. 

(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, 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: 

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. 

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) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(l) Related Information 

(1) Refer to European Aviation Safety 

Agency (EASA) Airworthiness Directive 

2012–0183R1, dated September 28, 2012, for 

related information, which can be found in 

the AD docket on the Internet at http://

www.regulations.gov. 

Issued in Renton, Washington, on August 

16, 2013. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–20845 Filed 8–26–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0701; Directorate 

Identifier 2013–NM–073–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 727 airplanes. 

This proposed AD is intended to 

complete certain mandated programs 

intended to support the airplane 

reaching its limit of validity (LOV) of 

the engineering data that support the 

established structural maintenance 

program. This proposed AD would 

require repetitive inspections for 

cracking of small repairs done on the 

vertical flange of the rib chord, 

repetitive inspections for cracking along 

the upper fillet radius of the rib chord, 

and a large repair or preventive 

modification if necessary. 

Accomplishment of a large repair or 

preventive modification would 

terminate the actions of the proposed 

AD. We are proposing this AD to 

prevent cracks in the rib upper chord, 

which could result in the inability of the 

wing structure to support the limit load 

condition, and consequent loss of 

structural integrity of the wing. 

DATES: We must receive comments on 

this proposed AD by October 11, 2013. 

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 proposed 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. You may 

review copies of the referenced service 

information at the FAA, Transport 

Airplane Directorate, 1601 Lind Avenue 

SW., Renton, Washington. 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; 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: 

Galib Abumeri, Aerospace Engineer, 

Airframe Branch, ANM–120L, FAA, Los 

Angeles Aircraft Certification Office 

(ACO), 3960 Paramount Blvd., Suite 

100, Lakewood, CA 90712–4137; phone: 

562–627–5324; fax: 562–672–5210; 

email: galib.abumeri@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposal. Send your comments to 

an address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2013–0701; Directorate Identifier 2013– 

NM–073–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 because of 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 

As described in FAA Advisory 

Circular 120–104 (http://www.faa.gov/

documentLibrary/media/Advisory_

Circular/120–104.pdf), several programs 

have been developed to support 

initiatives that will ensure the 

continued airworthiness of aging 

airplane structure. The last element of 

those initiatives is the requirement to 

establish a limit of validity (LOV) of the 


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