77376 Federal Register / Vol. 79, No. 247 / Wednesday, December 24, 2014 / Rules and Regulations 

information on the availability of this 

material at the FAA, call (816) 329–4148. 

(5) 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 

December 15, 2014. 

Earl Lawrence, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. 2014–29833 Filed 12–23–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0981; Directorate 

Identifier 2013–NM–032–AD; Amendment 

39–18036; AD 2014–24–03] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 97–11–07 

and AD 99–18–23, which apply to all 

The Boeing Company Model MD–90–30 

airplanes. AD 97–11–07 and AD 99–18– 

23 required revising the Airworthiness 

Limitations Section (ALS) of the 

Instructions for Continued 

Airworthiness to incorporate certain 

compliance times for principal 

structural element (PSE) inspections 

and replacement times for safe-life 

limited parts. This new AD also requires 

revising the maintenance or inspection 

program to incorporate a new PSE 

requirement for the rear spar caps of the 

horizontal stabilizer and its associated 

inspections, which would terminate 

certain inspections of the horizontal 

stabilizer rear spar. This AD was 

prompted by an analysis of data that 

identified a need to introduce a new 

PSE requirement for the rear spar caps 

of the horizontal stabilizer. We are 

issuing this AD to detect and correct 

fatigue cracking of PSEs and certain 

safe-life limited parts, which could 

adversely affect the structural integrity 

of the airplane. 

DATES: This AD is effective January 27, 

2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of January 27, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

this AD as of October 8, 1999 (64 FR 

48284, September 3, 1999). 

ADDRESSES: 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. 

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–2013– 

0981; 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 (phone: 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: 

Roger Durbin, Airframe Branch, ANM– 

120L, FAA, Los Angeles Aircraft 

Certification Office (ACO), 3960 

Paramount Boulevard, Lakewood, CA 

90712–4137; phone: 562–627–5233; fax: 

562–627–5210; email: roger.durbin@

faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 97–11–07, 

Amendment 39–10036 (62 FR 27941, 

May 22, 1997); and AD 99–18–23, 

Amendment 39–11289 (64 FR 48284, 

September 3, 1999). AD 97–11–07 and 

AD 99–18–23 applied to all The Boeing 

Company Model MD–90–30 airplanes. 

The NPRM published in the Federal 

Register on December 9, 2013 (78 FR 

73739). An action to reopen the 

comment period was issued on April 4, 

2014 (79 FR 20138, April 11, 2014). The 

NPRM was prompted by an analysis of 

data that identified a need to introduce 

a new PSE requirement for the rear spar 

caps of the horizontal stabilizer. The 

NPRM proposed to continue to require 

revising the maintenance or inspection 

program to incorporate certain 

compliance times for PSE inspections 

and replacement times for safe-life 

limited parts. The NPRM also proposed 

to require revising the maintenance or 

inspection program to incorporate a new 

PSE requirement for the rear spar caps 

of the horizontal stabilizer and its 

associated inspections. We are issuing 

this AD to detect and correct fatigue 

cracking of PSEs and certain safe-life 

limited parts, which could adversely 

affect the structural integrity of the 

airplane. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

have considered the comment received. 

One commenter, a private individual, 

supported the NPRM (78 FR 73739, 

December 9, 2013). 

Explanation of Changes Made to This 

AD 

In the NPRM (78 FR 73739, December 

9, 2013), we referred to McDonnell 

Douglas Airworthiness Limitations 

Instructions (ALI), Report No. MDC– 

94K9000, Revision 1, dated January 

1995; or McDonnell Douglas 

Airworthiness Limitations Instructions 

(ALI), Report No. MDC–94K9000, 

Revision 2, dated July 1996; as the 

appropriate sources of service 

information for certain requirements 

retained from AD 97–11–07, 

Amendment 39–10036 (62 FR 27941, 

May 22, 1997). We have changed 

paragraphs (g) and (h) of this AD by 

removing these references because this 

service information is out of date and no 

longer available. Instead, we have 

provided the option of using a method 

approved by the FAA to accomplish the 

actions in those paragraphs. We have 

also added a new paragraph (n) to this 

AD to provide credit for previous 

actions done using these earlier 

revisions. We have redesignated 

subsequent paragraphs accordingly. 

We have also replaced the text 

‘‘alternative inspections and inspection 

intervals’’ specified in paragraph (k) of 

the proposed AD (78 FR 73739, 

December 9, 2013) with the text 

‘‘alternative replacement times’’ in 

paragraph (k) of this AD in order to 

clarify that no alternative replacement 

times for certain safe-life limited parts 

may be approved, except as provided by 

paragraphs (l) and (o) of this AD. 

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Federal Register / Vol. 79, No. 247 / Wednesday, December 24, 2014 / Rules and Regulations 77377 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting this AD 

with the changes described previously 

and minor editorial changes. We have 

determined that these minor changes: 

• Are consistent with the intent that was 

proposed in the NPRM (78 FR 73739, 

December 9, 2013) for correcting the unsafe 

condition; and 

• Do not add any additional burden upon 

the public than was already proposed in the 

NPRM (78 FR 73739, December 9, 2013). 

Costs of Compliance 

We estimate that this AD affects 52 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per 

product 

Cost on U.S. 

operators 

Revise airworthiness limitations [retained actions from 

AD 97–11–07, Amendment 39–10036 (62 FR 

27941, May 22, 1997).

1 work-hour × 85 per hour = 85 ...... 0 85 4,420 

Revise airworthiness limitations [retained actions from 

AD 99–18–23, Amendment 39–11289 (64 FR 

48284, September 3, 1999).

1 work-hour × 85 per hour = 85 ...... 0 85 4,420 

Revise airworthiness limitations [new action] ............... 1 work-hour × 85 per hour = 85 ...... 0 85 4,420 

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 have 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 

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 

■ a. Removing Airworthiness Directive 

(AD) 97–11–07, Amendment 39–10036 

(62 FR 27941, May 22, 1997); and AD 

99–18–23, Amendment 39–11289 (64 

FR 48284, September 3, 1999); and 

■ b. Adding the following new AD: 

2014–24–03 The Boeing Company:

Amendment 39–18036; Docket No. 

FAA–2013–0981; Directorate Identifier 

2013–NM–032–AD. 

(a) Effective Date 

This AD is effective January 27, 2015. 

(b) Affected ADs 

This AD replaces AD 97–11–07, 

Amendment 39–10036 (62 FR 27941, May 22, 

1997); and AD 99–18–23, Amendment 39– 

11289 (64 FR 48284, September 3, 1999). 

(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 51, Standard Practices/

Structures; Code 55, Stabilizers. 

(e) Unsafe Condition 

This AD was prompted by an analysis of 

data that identified a need to introduce a new 

principal structural element (PSE) 

requirement for the rear spar caps of the 

horizontal stabilizer. We are issuing this AD 

to detect and correct fatigue cracking of PSEs 

and certain safe-life limited parts, which 

could adversely affect the structural integrity 

of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Revision of Airworthiness 

Limitations: Paragraph (a) of AD 97–11–07, 

Amendment 39–10036 (62 FR 27941, May 

22, 1997) 

This paragraph restates the requirements of 

paragraph (a) of AD 97–11–07, Amendment 

39–10036 (62 FR 27941, May 22, 1997). 

Within 180 days after June 26, 1997 (the 

effective date of AD 97–11–07), revise the 

Airworthiness Limitations Section of the 

Instructions for Continued Airworthiness to 

incorporate the Item, Location, and 

Inspection Interval of PSEs identified in 

paragraphs (g)(1) through (g)(3) of this AD. 

This may be accomplished by inserting a 

copy of this AD into the ALI, or by using a 

method approved by the Manager, Los 

Angeles Aircraft Certification Office (ACO), 

FAA. 

(1) For Item 53.30.02.3 at Skin Panels, 

station (STA) 237 to 1395 Fuselage Skin in 

Constant Section from Longeron 3 Left to 

Longeron 3 Right: the initial interval is 

60,000 landings. Repeat the inspection 

thereafter at intervals not to exceed 11,000 

landings. 

(2) For Item 53.30.02.4 at Skin Panels, STA 

237 to 1395 Fuselage Hoop Skin Splice in 

Constant Section from Longeron 5 Left to 

Longeron 5 Right: the initial interval is 

60,000 landings. Repeat the inspection 

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77378 Federal Register / Vol. 79, No. 247 / Wednesday, December 24, 2014 / Rules and Regulations 

thereafter at intervals not to exceed 30,000 

landings. 

(3) For Item 54.10.04.1 at Thrust Bulkhead, 

Pylon—STA Yn 170.5—Rear Spar and Engine 

Thrust Support Fitting (Upper and Lower): 

the initial interval is 15,000 landings. Repeat 

the inspection thereafter at intervals not to 

exceed 4,500 landings. 

(h) Retained Revision of Airworthiness 

Limitations: Paragraph (b) of AD 97–11–07, 

Amendment 39–10036 (62 FR 27941, May 

22, 1997) 

This paragraph restates the requirements of 

paragraph (b) of AD 97–11–07, Amendment 

39–10036 (62 FR 27941, May 22, 1997). 

Within 180 days after June 26, 1997 (the 

effective date of AD 97–11–07), revise the 

Airworthiness Limitations Section of the 

Instructions for Continued Airworthiness to 

incorporate the Item, Location, and 

Inspection Interval of PSE 55.13.01.1 at 

Plates/Skin—Upper STA Xh 27.2 Left to Xh 

27.2 Right—Upper Aft Skin Plank with 

Integral Stringers from Xh 7.234 to Xh 

26.859. The initial interval is 60,000 

landings. Repeat the inspection thereafter at 

intervals not to exceed 8,100 landings. This 

may be accomplished by inserting a copy of 

this AD into the ALI, or using a method 

approved by the Manager, Los Angeles ACO, 

FAA. 

(i) Retained Restriction on Alternative 

Inspections and Inspection Intervals: 

Paragraph (c) of AD 97–11–07, Amendment 

39–10036 (62 FR 27941, May 22, 1997) 

This paragraph restates the restriction on 

alternative inspections and inspection 

intervals required by paragraph (c) of AD 97– 

11–07, Amendment 39–10036 (62 FR 27941, 

May 22, 1997). Except as provided by 

paragraphs (l) and (o) of this AD: After the 

actions required by paragraphs (g) and (h) of 

this AD have been accomplished, no 

alternative inspections or inspection 

intervals may be approved for the parts 

specified in paragraphs (g) and (h) of this AD. 

(j) Retained Revision of Airworthiness 

Limitations of Safe-Life Limited Parts: 

Paragraph (a) of AD 99–18–23, Amendment 

39–11289 (64 FR 48284, September 3, 1999) 

This paragraph restates the requirements of 

paragraph (a) of AD 99–18–23, Amendment 

39–11289 (64 FR 48284, September 3, 1999). 

Within 180 days after October 8, 1999 (the 

effective date of AD 99–18–23, Amendment 

39–48284 (64 FR 48284, September 3, 1999)), 

revise the Airworthiness Limitations Section 

of the Instructions for Continued 

Airworthiness to incorporate the Part 

Number, Item, and Mandatory Replacement 

Time of certain safe-life limited parts by 

inserting McDonnell Douglas Airworthiness 

Limitations Instructions (ALI), Report No. 

MDC–94K9000, Revision 3, dated November 

1997, into the ALI. 

(k) Retained Restriction on Alternative 

Replacement Times: Paragraph (b) of AD 99– 

18–23, Amendment 39–11289 (64 FR 48284, 

September 3, 1999) 

This paragraph restates the restriction on 

alternative replacement times required by 

paragraph (b) of AD 99–18–23, Amendment 

39–11289 (64 FR 48284, September 3, 1999). 

Except as provided by paragraphs (l) and (o) 

of this AD: After the actions required by 

paragraph (j) of this AD have been 

accomplished, no alternative replacement 

times may be approved for the safe-life 

limited parts specified in McDonnell Douglas 

Airworthiness (Airworthiness Limitations 

Instructions (ALI) Report No. MDC–94K9000, 

Revision 3, dated November 1997. 

(l) New Requirements of This AD: Revision 

of the Maintenance Program 

Within 180 days after the effective date of 

this AD, revise the maintenance or inspection 

program, as applicable, to incorporate the 

tasks specified in Boeing MD–90 

Airworthiness Limitations Instructions (ALI), 

Report No. MDC–94K9000, Revision 6, dated 

September 2011. The compliance times for 

the initial compliance time and repetitive 

intervals for the tasks are stated in Boeing 

MD–90 Airworthiness Limitations 

Instructions (ALI), Report No. MDC– 

94K9000, Revision 6, dated September 2011. 

Doing the revision required by this paragraph 

terminates the revisions required by 

paragraphs (g), (h), and (j) of this AD. 

(m) New Restriction on Alternative Actions 

and Intervals 

After accomplishing the revision required 

by paragraph (l) of this AD, no alternative 

actions (e.g., inspections) or intervals may be 

used unless the actions or intervals are 

approved as an AMOC in accordance with 

the procedures specified in paragraph (o) of 

this AD. 

(n) Credit for Previous Actions 

(1) This paragraph provides credit for the 

actions required by paragraph (g) of this AD, 

if those actions were performed before the 

effective date of this AD using McDonnell 

Douglas Airworthiness Limitations 

Instructions (ALI), Report No. MDC– 

94K9000, Revision 1, dated January 1995. 

(2) This paragraph provides credit for the 

actions required by paragraph (h) of this AD, 

if those actions were performed before the 

effective date of this AD using McDonnell 

Douglas ALI, Report No. MDC–94K9000, 

Revision 2, dated July 1996. 

(o) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Los Angeles 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 (p) 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 

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 the 

approval must specifically refer to this AD. 

(4) AMOCs approved previously for AD 

97–11–07, Amendment 39–10036 (62 FR 

27941, May 22, 1997); and AD 99–18–23, 

Amendment 39–11289 (64 FR 48284, 

September 3, 1999); are approved as AMOCs 

for the corresponding provisions of this AD. 

(p) Related Information 

For more information about this AD, 

contact Roger Durbin, Airframe Branch, 

ANM–120L, FAA, Los Angeles ACO, 3960 

Paramount Boulevard, Lakewood, CA 90712– 

4137; phone: 562–627–5233; fax: 562–627– 

5210; email: roger.durbin@faa.gov. 

(q) 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 January 27, 2015. 

(i) Boeing MD–90 Airworthiness 

Limitations Instructions (ALI), Report No. 

MDC–94K9000, Revision 6, dated September 

2011. 

(ii) Reserved. 

(4) The following service information was 

approved for IBR on October 8, 1999 (64 FR 

48284, September 3, 1999). 

(i) McDonnell Douglas Airworthiness 

Limitations Instructions (ALI) Report No. 

MDC–94K9000, Revision 3, dated November 

1997. 

(ii) Reserved. 

(5) 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. 

(6) You may view this service information 

at 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 

November 19, 2014. 

Suzanne Masterson, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–30131 Filed 12–23–14; 8:45 am] 

BILLING CODE 4910–13–P 

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