Federal Register / Vol. 79, No. 165 / Tuesday, August 26, 2014 / Proposed Rules 50863 

(k) Incorporation of Critical Design 

Configuration Control Limitations (CDCCL) 

Items 

Within 60 days after the effective date of 

this AD, revise the maintenance or inspection 

program, as applicable, to incorporate the 

CDCCL items specified in Bombardier 

Temporary Revision ALI–112, dated January 

11, 2011, to Section 5–1, ‘‘Critical Design 

Configuration Control Limitations,’’ of Part 2, 

‘‘Airworthiness Limitation Items,’’ of 

Bombardier Q400 Dash 8 Maintenance 

Requirements Manual PSM 1–84–7. The 

maintenance program revision required by 

this paragraph may be done by inserting a 

copy of Bombardier Temporary Revision 

ALI–112, dated January 11, 2011, into the 

Airworthiness Limitation Items section of 

Bombardier Q400 Dash 8 Maintenance 

Requirements Manual PSM 1–84–7. When 

Bombardier Temporary Revision ALI–112, 

dated January 11, 2011, has been included in 

the general revisions of the manual, the 

general revisions may be inserted into the 

manual, and this temporary revision may be 

removed, provided the relevant information 

in the general revision is identical to that in 

Bombardier Temporary Revision ALI–112. 

(l) No Alternative Actions, Intervals, and 

CDCCLs 

After the maintenance or inspection 

program, as applicable, has been revised as 

required by paragraphs (j) and (k) of this AD, 

no alternative actions (e.g., inspections), 

intervals, or CDCCLs may be used unless the 

actions, intervals, or CDCCL are approved as 

an alternative method of compliance (AMOC) 

in accordance with the procedures specified 

in paragraph (o)(1) of this AD. 

(m) Exception to Certain Service Information 

Where the service information, Bombardier 

Service Bulletin 84–28–09, Revision D, dated 

December 21, 2012; and Bombardier Service 

Bulletin 84–28–15, dated August 15, 2012; 

specify contacting the manufacturer for 

corrective action during accomplishment of 

the actions in those service bulletins: Before 

further flight, repair the discrepancy using a 

method approved by the Manager, New York 

Aircraft Certification Office (ACO), FAA; or 

Transport Canada Civil Aviation (TCCA); or 

Bombardier, Inc.’s TCCA Design Approval 

Organization (DAO). If approved by the DAO, 

the approval must include the DAOauthorized signature. 

(n) Credit for Previous Actions 

This paragraph provides credit for actions 

required by paragraph (i)(1) of this AD, if 

those actions were performed before the 

effective date of this AD using Bombardier 

Service Bulletin 84–28–10, dated December 

6, 2011; or Revision A, dated May 15, 2012; 

which are not incorporated by reference in 

this AD. 

(o) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York Aircraft 

Certification Office (ACO), ANE–170, 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 ACO, send it to ATTN: 

Program Manager, Continuing Operational 

Safety, FAA, New York ACO, 1600 Stewart 

Avenue, Suite 410, Westbury, NY 11590; 

telephone 516–228–7300; fax 516–794–5531. 

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: 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, New York ACO, ANE–170, 

Engine and Propeller Directorate, FAA; or 

Transport Canada Civil Aviation (TCCA); or 

Bombardier, Inc.’s TCCA Design Approval 

Organization (DAO). If approved by the DAO, 

the approval must include the DAOauthorized signature. 

(p) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

Airworthiness Directive CF–2013–09R1, 

dated May 28, 2013, 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–2014–0583. 

(2) For service information identified in 

this AD, contact Bombardier, Inc., Q-Series 

Technical Help Desk, 123 Garratt Boulevard, 

Toronto, Ontario M3K 1Y5, Canada; 

telephone 416–375–4000; fax 416–375–4539; 

email thd.qseries@aero.bombardier.com; 

Internet http://www.bombardier.com. 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 August 

15, 2014. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–20263 Filed 8–25–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0584; Directorate 

Identifier 2014–NM–092–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

Airworthiness Directive (AD) 2014–09– 

05, for certain Airbus Model A330–200 

and –300 series airplanes, and Model 

A340–200 and –300 series airplanes. AD 

2014–09–05 currently requires 

repetitive inspections of certain sidestay 

upper cardan pins of the main landing 

gear (MLG), and associated nuts and 

retainer assemblies, and pin 

replacement if necessary. Since we 

issued AD 2014–09–05, we have 

determined that a previously optional 

measurement is necessary to address the 

identified unsafe condition. We are 

proposing this AD to detect and correct 

migration of the sidestay upper cardan 

pin, which could result in 

disconnection of the sidestay upper arm 

from the airplane structure, and could 

result in a landing gear collapse and 

consequent damage to the airplane and 

injury to occupants. 

DATES: We must receive comments on 

this proposed AD by October 10, 2014. 

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 Airbus SAS— 

Airworthiness Office—EAL, 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 

96; fax +33 5 61 93 45 80; email 

airworthiness.A330-A340@airbus.com; 

Internet http://www.airbus.com. You 

may view this referenced service 

information at the FAA, Transport 

Airplane Directorate, 1601 Lind Avenue 

SW., Renton, WA. For information on 

the availability of this material at the 

FAA, call 425–227–1221. 

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–2014– 

0584; or in person at the Docket 

Management Facility between 9 a.m. 

and 5 p.m., Monday through Friday, 


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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: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–1138; 

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–2014–0584; Directorate Identifier 

2014–NM–092–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 April 16, 2014, we issued AD 

2014–09–05, Amendment 39–17840 (79 

FR 23909, April 29, 2014). AD 2014–09– 

05 requires actions intended to address 

an unsafe condition on certain Airbus 

Model A330–200 and –300 series 

airplanes, and Model A340–200 and 

–300 series airplanes. 

Since we issued AD 2014–09–05, 

Amendment 39–17840 (79 FR 23909, 

April 29, 2014), we have determined 

that the optional measurement specified 

in that AD is necessary to address the 

identified unsafe condition. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2014–0066, 

corrected March 20, 2014 (referred to 

after this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

on certain Airbus Model A330–200 and 

–300 series airplanes, and Model A340– 

200 and –300 series airplanes. The 

MCAI states: 

An A330 aeroplane equipped with Basic 

(main landing gear) MLG was rolling out after 

landing when it experienced a nose wheel 

steering fault (unrelated to the safety subject 

addressed by this [EASA] AD), which 

resulted in the crew stopping the aeroplane 

on the taxiway after vacating the runway. 

The subsequent investigation revealed that 

the right-hand MLG sidestay upper cardan 

pin had migrated out of position. The 

sidestay upper cardan nut and retainer were 

found in the landing gear bay detached from 

the upper cardan pin. The nut and the 

retainer were still bolted together. 

This condition, if not detected and 

corrected, could lead to a complete migration 

of the sidestay upper cardan pin and a 

disconnection of the sidestay upper arm from 

the aeroplane structure, possibly resulting in 

MLG collapse with consequent damage to the 

aeroplane and injury to occupants. 

To address this potential condition, Airbus 

published Alert Operators Transmission 

(AOT) A32L003–14, providing inspection 

instructions. 

For the reasons described above, this 

[EASA] AD requires accomplishment of 

repetitive [detailed inspections for visible 

chrome] of the MLG upper cardan pin, nut 

and retainer [and pin replacement if 

necessary]. This [EASA] AD also requires 

accomplishment of a gap check between 

wing rear spar fitting lugs and the bush 

flanges [and corrective actions if necessary. 

Corrective actions include repair or 

replacement of the cardan pin assembly]. 

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–2014– 

0584. 

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. 

‘‘Contacting the Manufacturer’’ 

Paragraph in This Proposed AD 

Since late 2006, we have included a 

standard paragraph titled ‘‘Airworthy 

Product’’ in all MCAI ADs in which the 

FAA develops an AD based on a foreign 

authority’s AD. 

The MCAI or referenced service 

information in an FAA AD often directs 

the owner/operator to contact the 

manufacturer for corrective actions, 

such as a repair. Briefly, the Airworthy 

Product paragraph allowed owners/

operators to use corrective actions 

provided by the manufacturer if those 

actions were FAA-approved. In 

addition, the paragraph stated that any 

actions approved by the State of Design 

Authority (or its delegated agent) are 

considered to be FAA-approved. 

In an NPRM having Directorate 

Identifier 2012–NM–101–AD (78 FR 

78285, December 26, 2013), we 

proposed to prevent the use of repairs 

that were not specifically developed to 

correct the unsafe condition, by 

requiring that the repair approval 

provided by the State of Design 

Authority or its delegated agent 

specifically refer to the FAA AD. This 

change was intended to clarify the 

method of compliance and to provide 

operators with better visibility of repairs 

that are specifically developed and 

approved to correct the unsafe 

condition. In addition, we proposed to 

change the phrase ‘‘its delegated agent’’ 

to include a design approval holder 

(DAH) with State of Design Authority 

design organization approval (DOA), as 

applicable, to refer to a DAH authorized 

to approve required repairs for the 

proposed AD. 

One commenter to the NPRM having 

Directorate Identifier 2012–NM–101–AD 

(78 FR 78285, December 26, 2013) stated 

the following: ‘‘The proposed wording, 

being specific to repairs, eliminates the 

interpretation that Airbus messages are 

acceptable for approving minor 

deviations (corrective actions) needed 

during accomplishment of an AD 

mandated Airbus service bulletin.’’ 

This comment has made the FAA 

aware that some operators have 

misunderstood or misinterpreted the 

Airworthy Product paragraph to allow 

the owner/operator to use messages 

provided by the manufacturer as 

approval of deviations during the 

accomplishment of an AD-mandated 

action. The Airworthy Product 

paragraph does not approve messages or 

other information provided by the 

manufacturer for deviations to the 

requirements of the AD-mandated 

actions. The Airworthy Product 

paragraph only addresses the 

requirement to contact the manufacturer 

for corrective actions for the identified 

unsafe condition and does not cover 

deviations from other AD requirements. 

However, deviations to AD-required 

actions are addressed in 14 CFR 39.17, 

and anyone may request the approval 

for an alternative method of compliance 

to the AD-required actions using the 

procedures found in 14 CFR 39.19. 

To address this misunderstanding and 

misinterpretation of the Airworthy 

Product paragraph, we have changed the 

paragraph and retitled it ‘‘Contacting the 


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Manufacturer.’’ This paragraph now 

clarifies that for any requirement in this 

proposed AD to obtain corrective 

actions from a manufacturer, the actions 

must be accomplished using a method 

approved by the FAA, the European 

Aviation Safety Agency (EASA), or 

Airbus’s EASA DOA. 

The Contacting the Manufacturer 

paragraph also clarifies that, if approved 

by the DOA, the approval must include 

the DOA-authorized signature. The DOA 

signature indicates that the data and 

information contained in the document 

are EASA-approved, which is also FAAapproved. Messages and other 

information provided by the 

manufacturer that do not contain the 

DOA-authorized signature approval are 

not EASA-approved, unless EASA 

directly approves the manufacturer’s 

message or other information. 

This clarification does not remove 

flexibility previously afforded by the 

Airworthy Product paragraph. 

Consistent with long-standing FAA 

policy, such flexibility was never 

intended for required actions. This is 

also consistent with the 

recommendation of the Airworthiness 

Directive Implementation Aviation 

Rulemaking Committee to increase 

flexibility in complying with ADs by 

identifying those actions in 

manufacturers’ service instructions that 

are ‘‘Required for Compliance’’ with 

ADs. We continue to work with 

manufacturers to implement this 

recommendation. But once we 

determine that an action is required, any 

deviation from the requirement must be 

approved as an alternative method of 

compliance. 

We also have decided not to include 

a generic reference to either the 

‘‘delegated agent’’ or ‘‘design approval 

holder (DAH) with State of Design 

Authority design organization 

approval,’’ but instead we have 

provided the specific delegation 

approval granted by the State of Design 

Authority for the DAH throughout this 

proposed AD. 

Costs of Compliance 

We estimate that this proposed AD 

affects 83 airplanes of U.S. registry. 

The actions that are required by AD 

2014–09–05, Amendment 39–17840 (79 

FR 23909, April 29, 2014), and retained 

in this proposed AD take about 1 workhour per product, at an average labor 

rate of $85 per work-hour. Required 

parts cost $0 per product. Based on 

these figures, the estimated cost of the 

actions that are required by AD 2014– 

09–05 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 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 $7,055, or $85 per product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 4 work-hours and require parts 

costing $7,530, for a cost of $7,870 per 

product. We have no way of 

determining the number of aircraft that 

might need these actions. 

Paperwork Reduction Act 

A federal agency may not conduct or 

sponsor, and a person is not required to 

respond to, nor shall a person be subject 

to penalty for failure to comply with a 

collection of information subject to the 

requirements of the Paperwork 

Reduction Act unless that collection of 

information displays a current valid 

OMB control number. The control 

number for the collection of information 

required by this AD is 2120–0056. The 

paperwork cost associated with this AD 

has been detailed in the Costs of 

Compliance section of this document 

and includes time for reviewing 

instructions, as well as completing and 

reviewing the collection of information. 

Therefore, all reporting associated with 

this AD is mandatory. Comments 

concerning the accuracy of this burden 

and suggestions for reducing the burden 

should be directed to the FAA at 800 

Independence Ave. SW., Washington, 

DC 20591, ATTN: Information 

Collection Clearance Officer, AES–200. 

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. Amend § 39.13 by removing 

Airworthiness Directive (AD) 2014–09– 

05, Amendment 39–17840 (79 FR 

23909, April 29, 2014), and adding the 

following new AD: 

Airbus: Docket No. FAA–2014–0584; 

Directorate Identifier 2014–NM–092–AD. 

(a) Comments Due Date 

We must receive comments by October 10, 

2014. 

(b) Affected ADs 

This AD replaces AD 2014–09–05, 

Amendment 39–17840 (79 FR 23909, April 

29, 2014). 

(c) Applicability 

This AD applies to the airplanes identified 

in paragraphs (c)(1) and (c)(2) of this AD, 

certificated in any category. 

(1) Airbus Model A330–201, A330–202, 

A330–203, A330–223, A330–243, A330–301, 

A330–302, A330–303, A330–321, A330–322, 

A330–323, A330–341, A330–342, and A330– 

343 airplanes, all manufacturer serial 

numbers (MSNs), equipped with basic 

(201252 series) main landing gear (MLG), or 

growth (201490 series) MLG. 


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(2) Airbus Model A340–211, A340–212, 

A340–213, A340–311, A340–312, and A340– 

313 airplanes, all MSNs, equipped with basic 

(201252 series) MLG or growth (201490 

series) MLG. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 32, Landing Gear. 

(e) Reason 

This AD was prompted by a report of a 

sidestay upper cardan pin of the MLG 

migrating out of position. We are issuing this 

AD to detect and correct migration of the 

sidestay upper cardan pin, which could 

result in disconnection of the sidestay upper 

arm from the airplane structure, and which 

could result in a landing gear collapse and 

consequent damage to the airplane and injury 

to occupants. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Repetitive Detailed Inspections 

With No Changes 

This paragraph restates the requirements of 

paragraph (g) of AD 2014–09–05, 

Amendment 39–17840 (79 FR 23909, April 

29, 2014), with no changes. 

(1) For airplanes identified in paragraphs 

(g)(1)(i) and (g)(1)(ii) of this AD on which the 

affected MLG has exceeded 8 years since first 

overhaul, as of May 14, 2014 (the effective 

date of AD 2014–09–05, Amendment 39– 

17840 (79 FR 23909, April 29, 2014), except 

those MLG that have had a second overhaul: 

Within 30 days after May 14, 2014, 

accomplish a detailed inspection for visible 

chrome of each affected MLG sidestay upper 

cardan pin, and associated nut and retainer 

assembly, in accordance with the 

instructions of Airbus Alert Operators 

Transmission (AOT) A32L003–14, dated 

March 10, 2014, including Appendices 1, 2, 

and 3 (the issue date is not specified on the 

appendices). 

(i) Airplanes equipped with any MLG 

sidestay upper cardan pin subassembly part 

number (P/N) 201267202 (on 201252 series 

MLG). 

(ii) Airplanes equipped with any MLG 

sidestay upper cardan pin subassembly P/N 

201483202 (on 201490 series MLG). 

(2) If, during any inspection required by 

paragraph (g)(1) of this AD, no pin chrome 

is visible inboard of the wing rear spar fitting 

lug, repeat the detailed inspection for visible 

chrome specified in paragraph (g)(1) of this 

AD thereafter at intervals not to exceed 10 

days. 

(3) If, during any inspection required by 

paragraphs (g)(1) or (g)(2) of this AD, pin 

chrome is visible inboard of the wing rear 

spar fitting lug, before further flight, replace 

the affected cardan pin assembly, in 

accordance with the instructions of Airbus 

AOT A32L003–14, dated March 10, 2014, 

including Appendices 1, 2, and 3 (the issue 

date is not specified on the appendices). 

Replacement of the affected cardan pin 

assembly terminates the repetitive 

inspections required by paragraph (g)(2) of 

this AD. 

Note 1 to paragraph (g) of this AD: MLG 

sidestay upper cardan pin subassembly P/N 

201267202 (found in Airbus Illustrated Parts 

Catalogue (IPC) as item 32–11–18–01) 

includes the cardan pin P/N 201267600. 

MLG sidestay upper cardan pin subassembly 

P/N 201483202 (found in Airbus IPC as item 

32–11–18–01) includes the cardan pin P/N 

201483600. 

(h) New Terminating Action—Gap Check 

Within 4 months after the effective date of 

this AD: Measure the cardan pin clearance 

dimensions (gap check) and do the 

applicable corrective action specified in 

paragraph (h)(1) or (h)(2) of this AD. 

Measuring the gap check and doing the 

applicable corrective action specified in 

paragraph (h)(1) or (h)(2) of this AD, as 

applicable, terminates the repetitive 

inspections required by paragraphs (g)(1) and 

(g)(2) of this AD for that sidestay upper 

cardan pin, nut, and retainer only. The 

measurement must be done in accordance 

with Airbus AOT A32L003–14, dated March 

10, 2014, including Appendices 1, 2, and 3 

(the issue date is not specified on the 

appendices). 

(1) If the total clearance dimension (gap 

check result) is equal to or greater than 1.5 

mm, before further flight, replace the cardan 

pin assembly, in accordance with Airbus 

AOT A32L003–14, dated March 10, 2014, 

including Appendices 1, 2, and 3 (the issue 

date is not specified on the appendices). 

(2) If the total clearance dimension (gap 

check) is less than 1.5 mm but greater than 

0.6 mm, do the actions specified in 

paragraphs (h)(2)(i) and (h)(2)(ii) of this AD. 

(i) Before further flight, send the 

information (Appendix 2 proforma, 

photographs, and the movement traceability 

sheet) specified in paragraph 4.2.3, 

‘‘Findings,’’ of Airbus AOT A32L003–14, 

dated March 10, 2014, including Appendices 

1, 2, and 3, to Airbus at the address specified 

in Appendix 2 of Airbus AOT A32L003–14, 

dated March 10, 2014. 

(ii) Within 30 days after accomplishing the 

gap check, repair using a method approved 

by the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

the European Aviation Safety Agency 

(EASA); or Airbus’s EASA Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(i) New Reporting of Inspection Results 

For airplanes on which a gap check 

specified in paragraph (h) of this AD has 

been done: Except as required by paragraph 

(h)(2)(i) of this AD, at the applicable time 

specified in paragraphs (i)(1) and (i)(2) of this 

AD, report all findings (including no 

findings) to Airbus, in accordance with 

Airbus AOT A32L003–14, dated March 10, 

2014, including Appendices 1, 2, and 3, (the 

issue date is not specified on the 

appendices). 

(1) If the gap check was done on or after 

the effective date of this AD: Submit the 

report within 30 days after the inspection. 

(2) If the gap check was done before the 

effective date of this AD: Submit the report 

within 30 days after the effective date of this 

AD. 

(j) 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: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1138; 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) 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 Airbus’s EASA Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(3) Reporting Requirements: A federal 

agency may not conduct or sponsor, and a 

person is not required to respond to, nor 

shall a person be subject to a penalty for 

failure to comply with a collection of 

information subject to the requirements of 

the Paperwork Reduction Act unless that 

collection of information displays a current 

valid OMB Control Number. The OMB 

Control Number for this information 

collection is 2120–0056. Public reporting for 

this collection of information is estimated to 

be approximately 5 minutes per response, 

including the time for reviewing instructions, 

completing and reviewing the collection of 

information. All responses to this collection 

of information are mandatory. Comments 

concerning the accuracy of this burden and 

suggestions for reducing the burden should 

be directed to the FAA at: 800 Independence 

Ave. SW., Washington, DC 20591, Attn: 

Information Collection Clearance Officer, 

AES–200. 

(k) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) European 

Aviation Safety Agency Airworthiness 

Directive 2014–0066 (Corrected March 20, 

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– 

2014–0584. 

(2) For service information identified in 

this AD, contact Airbus SAS, Airworthiness 

Office—EAL, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone +33 


tkelley on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 79, No. 165 / Tuesday, August 26, 2014 / Proposed Rules 50867 

5 61 93 36 96; fax +33 5 61 93 45 80; email 

airworthiness.A330-A340@airbus.com; 

Internet http://www.airbus.com. 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 August 

15, 2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–20262 Filed 8–25–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0572; Directorate 

Identifier 2014–NM–027–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 supersede 

Airworthiness Directive (AD) 98–22–10, 

which applies to certain The Boeing 

Company Model 737–100, –200, –200C, 

and –300 series airplanes. AD 98–22–10 

currently requires repetitive inspections 

for cracking of the aft frame and frame 

support structure of the forward service 

doorway, and repair if necessary. AD 

98–22–10 also provides for an optional 

terminating action for the repetitive 

inspection requirements of that AD. 

Since we issued AD 98–22–10, we have 

determined that additional inspections 

are needed, and that additional 

airplanes may be subject to the 

identified unsafe condition. This 

proposed AD would add inspections 

and add airplanes to the applicability. 

For certain airplanes, this proposed AD 

provides a preventive modification, 

which would terminate the repetitive 

inspections. We are proposing this AD 

to detect and correct fatigue cracking of 

the aft frame and frame support 

structure of the forward service doorway 

around the six doorstop fittings, which 

could result in door deflection and loss 

of pressurization. 

DATES: We must receive comments on 

this proposed AD by October 10, 2014. 

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 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–2014– 

0572; 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: 

Alan Pohl, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; phone 425–917–6450; fax 

425–917–6590; email: alan.pohl@

faa.gov. 

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–2014–0572; Directorate Identifier 

2014–NM–027–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 

On October 19, 1998, we issued AD 

98–22–10, Amendment 39–10858 (63 

FR 57240, October 27, 1998), for certain 

The Boeing Company Model 737–100, 

–200, –200C, and –300 series airplanes. 

AD 98–22–10 requires repetitive 

inspections to detect cracking of the aft 

frame and aft frame support structure of 

the forward service doorway, and repair 

if necessary. AD 98–22–10 resulted from 

reports of fatigue cracking of the aft 

frame and frame support structure of the 

forward service doorway. We issued AD 

98–22–10 to prevent fatigue cracking of 

the aft frame and frame support 

structure of the forward service 

doorway, which could result in loss of 

the door, and consequent rapid 

decompression of the fuselage. 

Tables 9 through 12 in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 737–53A1108, Revision 7, 

dated July 7, 2014, specify post-repair 

inspections, which may be used in 

support of compliance with section 

121.1109(c)(2) or 129.109(b)(2) of the 

Federal Aviation Regulations (14 CFR 

121.1109(c)(2) or 129.109(b)(2)). 

However, this NPRM does not propose 

to require those post-repair inspections. 

This difference has been coordinated 

with Boeing. 

Actions Since AD 98–22–10, 

Amendment 39–10858 (63 FR 57240, 

October 27, 1998), Was Issued 

Since we issued AD 98–22–10, 

Amendment 39–10858 (63 FR 57240, 

October 27, 1998), we received reports 

of cracking in the forward galley service 

doorway surround structure between 

body station (STA) 332.1 and STA 344, 

which are outside the inspection area of 

AD 98–22–10, and we have received 

reports that cracking has been 

discovered on airplanes outside the 

applicability of AD 98–22–10. We have 

determined that additional inspections 

are needed, and that additional 

airplanes are subject to the identified 

unsafe condition. 

Relevant Service Information 

We reviewed Boeing Alert Service 

Bulletin 737–53A1108, Revision 7, 

dated July 7, 2014. For information on 

the procedures and compliance times, 


tkelley on DSK3SPTVN1PROD with PROPOSALS