Federal Register / Vol. 79, No. 138 / Friday, July 18, 2014 / Proposed Rules 41943 

total flight hours since first flight of the 

airplane: Do the inspection within 1,500 

flight cycles or 3,000 flight hours after the 

effective date of this AD, whichever occurs 

first. 

(2) For airplanes that, as of the effective 

date of this AD, have accumulated 27,700 or 

more total flight cycles or 55,400 or more 

total flight hours, but fewer than 44,000 total 

flight cycles or 88,000 total flight hours since 

first flight of the airplane: Do the inspection 

within 3,000 flight cycles or 6,000 flight 

hours after the effective date of this AD, 

without exceeding 45,500 total flight cycles 

or 91,000 total flight hours since first flight 

of the airplane, whichever occurs first. 

(3) For airplanes that, as of the effective 

date of this AD, have accumulated fewer than 

27,700 total flight cycles and less than 55,400 

total flight hours since first flight of the 

airplane: Do the inspection before the 

accumulation of 30,700 total flight cycles or 

61,400 total flight hours since first flight of 

the airplane, whichever occurs first. 

(h) Corrective Action 

If any crack is found during any inspection 

required by this AD: Before further flight, 

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 DOAauthorized signature. 

(i) Optional Modification 

Accomplishing the modification of the 

splice plate of the FR47 butt joint in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

53–1271, dated December 18, 2012, 

constitutes terminating action for the 

repetitive inspections required by paragraph 

(g) 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 

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: Sanjay Ralhan, 

Aerospace Engineer, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, 1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: 425–227–1405; 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. 

(k) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2013–0203, dated 

September 6, 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 it in Docket No. 

FAA–2014–0453. 

(2) For service information identified in 

this AD, contact Airbus, Airworthiness 

Office—EAS, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone +33 

5 61 93 36 96; fax +33 5 61 93 44 51; email 

account.airworth-eas@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 July 13, 

2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–16950 Filed 7–17–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0450; Directorate 

Identifier 2013–NM–250–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 MD–90–30 

airplanes. This proposed AD was 

prompted by reports of cracks 

emanating from the aft-most barrel nut 

holes of the left and right upper rear 

spar caps of the horizontal stabilizer. 

This proposed AD would require 

repetitive high frequency eddy current 

(ETHF) inspections for cracks in the 

areas around the two aft-most barrel nut 

holes of the upper rear spar caps, and 

corrective action if necessary; and 

repetitive ETHF inspections for cracks 

in the areas around the two aft-most 

barrel nut holes of any repaired or 

replaced upper rear spar cap, and 

corrective actions if necessary. We are 

proposing this AD to detect and correct 

such cracks, which could propagate 

until the upper rear spar cap severs, and 

result in failure of the horizontal 

stabilizer upper center or aft skin panel 

and adversely affect the structural 

integrity of the airplane. 

DATES: We must receive comments on 

this proposed AD by September 2, 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, 3855 

Lakewood Boulevard, MC D800–0019, 

Long Beach, CA 90846–0001; telephone 

206–544–5000, extension 2; fax 206– 

766–5683; Internet https://

www.myboeingfleet.com. You may view 

this referenced service information at 

the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., 

Renton, WA. For information on the 

availability of this material at the FAA, 

call 425 227–1221. 

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– 

0450; 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: 

George Garrido, Aerospace Engineer, 

Airframe Branch, ANM–120L, FAA, Los 

Angeles Aircraft Certification Office, 

3960 Paramount Boulevard, Lakewood, 

CA 90712–4137; phone: 562–627–5357; 

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41944 Federal Register / Vol. 79, No. 138 / Friday, July 18, 2014 / Proposed Rules 

fax: 562–627–5210; email: 

george.garrido@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– 

2014–0450; Directorate Identifier 2013– 

NM–250–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 

We have received reports of cracks 

emanating from the aft-most barrel nut 

holes of the left and right upper rear 

spar caps of the horizontal stabilizer. 

One airplane had accumulated 40,144 

total flight hours and 32,253 total 

landing cycles, while another airplane 

had accumulated 58,296 total flight 

hours and 43,512 total landing cycles. 

Investigations have determined that the 

cracks were caused by fatigue. In both 

cases, the cracks originated inside of the 

barrel nut holes, and radiated vertically 

and in the aft direction from the barrel 

nut holes. This condition, if not 

corrected, could result in cracks in the 

horizontal stabilizer, which could 

propagate until it severs the upper rear 

spar cap, and result in failure of the 

horizontal stabilizer upper center or aft 

skin panel and adversely affect the 

structural integrity of the airplane. 

Relevant Service Information 

We reviewed Boeing Alert Service 

Bulletin MD90–55A017, dated 

September 27, 2013. For information on 

the procedures and compliance times, 

see this service information at http://

www.regulations.gov by searching for 

Docket No. FAA–2014–0450. 

FAA’s Determination 

We are proposing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type design. 

Proposed AD Requirements 

This proposed AD would require 

accomplishing repetitive high frequency 

eddy current (ETHF) inspections for 

cracks of the areas around the aft-most 

barrel nut holes of the upper rear spar 

caps, and corrective actions if necessary; 

and repetitive ETHF inspections for 

cracks at the two aft-most barrel nut 

holes of the repaired or replaced upper 

rear spar cap, and corrective actions if 

necessary. 

The phrase ‘‘corrective actions’’ is 

used in this proposed AD. ‘‘Corrective 

actions’’ are actions that correct or 

address any condition found. Corrective 

actions in an AD could include, for 

example, repairs. 

Difference Between This Proposed AD 

and the Service Information 

Table 1 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin MD90–55A017, dated 

September 27, 2013, specifies postrepair inspections of the upper rear spar 

cap of the aft flange that has been splicerepaired, 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 14 CFR 129.109(b)(2)). 

However, this NPRM does not propose 

to require those post-repair inspections. 

This difference has been coordinated 

with Boeing. 

Costs of Compliance 

We estimate that this proposed AD 

affects 52 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 

Inspection ............................................. 9 work-hours X $85 per hour = $765 

per inspection cycle.

$1,410 ................... $2,175 per inspection cycle.Up to $113,100 per 

inspection cycle. 

We estimate the following costs to do 

any necessary repairs and replacements 

that would be required based on the 

results of the proposed inspection. We 

have no way of determining the number 

of aircraft that might need these repairs 

and replacements: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per product 

Repair (per side) ................................................. 368 work-hours X $85 per hour = $31,280 ...... Up to $90,129 ............. Up to $121,409. 

Replacement ....................................................... 368 work-hours X $85 per hour = $31,280 ...... $81,764 ....................... $113,044. 

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 

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Federal Register / Vol. 79, No. 138 / Friday, July 18, 2014 / Proposed Rules 41945 

proposed AD would not have a 

substantial direct effect on the States, on 

the relationship between the national 

Government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify this proposed regulation: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Is not a ‘‘significant rule’’ under 

the DOT Regulatory Policies and 

Procedures (44 FR 11034, February 26, 

1979), 

(3) Will not affect intrastate aviation 

in Alaska, and 

(4) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 14 CFR part 

39 as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

The Boeing Company: Docket No. FAA– 

2014–0450; Directorate Identifier 2013 

NM–250–AD. 

(a) Comments Due Date 

We must receive comments by September 

2, 2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all The Boeing 

Company Model MD–90–30 airplanes, 

certificated in any category. 

(d) Subject 

Air Transport Association (ATA) of 

America Code Stabilizers, 55. 

(e) Unsafe Condition 

This AD was prompted by reports of cracks 

emanating from the aft-most barrel nut holes 

of the left and right upper rear spar caps of 

the horizontal stabilizer. We are issuing this 

AD to detect and correct cracks in the 

horizontal stabilizer, which could propagate 

until the upper rear spar cap severs, and 

result in failure of the horizontal stabilizer 

upper center or aft skin panel and adversely 

affect the structural integrity of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection 

At the applicable compliance time 

specified in paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Alert Service Bulletin MD90–55A017, 

dated September 27, 2013, except as 

provided by paragraph (i) of this AD: Do a 

high frequency eddy current inspection 

(ETHF) for cracks in the areas around the two 

aft-most barrel nut holes of the upper rear 

spar cap; and do all applicable corrective 

actions; in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin MD90–55A017, dated 

September 27, 2013. Thereafter, repeat the 

ETHF inspection at the applicable time 

specified in paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Alert Service Bulletin MD90–55A017, 

dated September 27, 2013. Do all corrective 

actions before further flight. 

(h) Post-Repair/Replacement Actions 

For airplanes on which a splice repair or 

replacement was done as specified in Boeing 

Alert Service Bulletin MD90–55A017: At the 

applicable compliance time specified in 

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

Alert Service Bulletin MD90–55A017, dated 

September 27, 2013, do an ETHF inspection 

for cracks at the two aft-most barrel nut holes 

of any repaired or replaced upper rear spar 

cap, in accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

MD90–55A017, dated September 27, 2013. 

Thereafter, repeat the ETHF inspection at the 

applicable time specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin MD90–55A017, dated September 27, 

2013. If any cracking is found, before further 

flight, do the repair or replacement, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

MD90–55A017, dated September 27, 2013. 

(i) Post-Repair Inspections 

The post-repair inspections of the upper 

rear spar cap of the aft flange that has been 

splice-repaired specified in Table 1 of 

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

Alert Service Bulletin MD90–55A017, dated 

September 27, 2013, are not required by this 

AD. 

Note 1 to paragraph (h) of this AD: The 

damage tolerance inspections (post-repair 

inspections of the upper rear spar cap aft 

flange) specified in Table 1 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin MD90–55A017, dated September 27, 

2013, 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 14 CFR 129.109(b)(2)). The 

corresponding actions specified in the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin MD90–55A017, dated 

September 27, 2013, are not required by this 

AD. 

(j) Exception to the Service Information 

Where Boeing Alert Service Bulletin 

MD90–55A017, dated September 27, 2013, 

specifies a compliance time ‘‘after the 

original issue date of this service bulletin,’’ 

this AD requires compliance within the 

specified compliance time after the effective 

date of this AD. 

(k) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Los Angeles Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in 

paragraph (l)(1) 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. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Los Angeles 

ACO, to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane, and 14 

CFR 25.571, Amendment 45, and the 

approval must specifically refer to this AD. 

(l) Related Information 

(1) For more information about this AD, 

contact George Garrido, Aerospace Engineer, 

Airframe Branch, ANM–120L, FAA, Los 

Angeles Aircraft Certification Office, 3960 

Paramount Boulevard, Lakewood, CA 90712– 

4137; phone: 562–627–5357; fax: 562–627– 

5210; email: george.garrido@faa.gov. 

(2) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, 3855 Lakewood Boulevard, MC 

D800 0019, Long Beach, CA 90846–0001; 

telephone 206–544–5000, extension 2; fax 

206–766–5683; Internet https://

www.myboeingfleet.com. You may view this 

referenced service information at the FAA, 

Transport Airplane Directorate, 1601 Lind 

Avenue SW., Renton, WA. For information 

on the availability of this material at the 

FAA, call 425–227–1221. 

Issued in Renton, Washington, on July 11, 

2014. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–16942 Filed 7–17–14; 8:45 am] 

BILLING CODE 4910–13–P 

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