Federal Register / Vol. 78, No. 211 / Thursday, October 31, 2013 / Rules and Regulations 65163 

14 CFR part 91, subpart K, we suggest that 

you notify your principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office or 

certificate holding district office, before 

operating any aircraft complying with this 

AD through an AMOC. 

(g) Additional Information 

(1) The subject of this AD is addressed in 

European Aviation Safety Agency (EASA) AD 

No. 2009–0037–E, dated February 19, 2009. 

You may view the EASA AD on the internet 

in the AD Docket at http://

www.regulations.gov. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 7250: Turbine Section. 

(i) 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. 

(i) Agusta Bollettino Tecnico No. 109–129, 

dated February 16, 2009. 

(ii) Reserved. 

(3) For Agusta service information 

identified in this AD, contact Agusta 

Westland, Customer Support & Services, Via 

Per Tornavento 15, 21019 Somma Lombardo 

(VA) Italy, ATTN: Giovanni Cecchelli; 

telephone 39–0331–711133; fax 39 0331 

711180; or at http://

www.agustawestland.com/technicalbullettins. 

(4) You may review this service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 2601 

Meacham Blvd., Room 663, Fort Worth, 

Texas 76137. 

(5) You may also 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 Fort Worth, Texas, on September 

20, 2013. 

Scott A. Horn, 

Acting Directorate Manager, Rotorcraft 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–24038 Filed 10–30–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0454; Directorate 

Identifier 2009–SW–81–AD; Amendment 39– 

17621; AD 2013–20–15] 

RIN 2120–AA64 

Airworthiness Directives; Sikorsky 

Aircraft Corporation-Manufactured 

(Sikorsky) Model Helicopters (Type 

Certificate Currently Held by Erickson 

Air-Crane Incorporated) 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 97–19–10 

for Sikorsky Aircraft Corporationmanufactured Model S–64E helicopters 

(type certificate currently held by 

Erickson Air-Crane Incorporated 

(Erickson)). AD 97–19–10 required 

inspecting and reworking the main 

gearbox (MGB) assembly second stage 

lower planetary plate (plate). This 

action establishes or reduces the life 

limits for certain flight-critical 

components, removes from service 

various parts, requires repetitive 

inspections and other corrective actions, 

and requires replacing any cracked part 

discovered during an inspection. This 

AD is prompted by further analysis 

performed by the current type certificate 

holder and the service history of certain 

parts. The actions specified in this AD 

are intended to prevent a crack in a 

flight critical component, failure of a 

critical part, and subsequent loss of 

control of the helicopter. 

DATES: This AD is effective December 5, 

2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain document listed in this AD 

as of December 5, 2013. 

ADDRESSES: For service information 

identified in this AD, contact Erickson 

Air-Crane Incorporated, ATTN: Chris 

Erickson, Director of Regulatory 

Compliance, 3100 Willow Springs Rd, 

P.O. Box 3247, Central Point, OR 97502, 

telephone (541) 664–5544, fax (541) 

664–2312, email address cerickson@

ericksonaircrane.com. You may review 

a copy of the referenced service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 

2601 Meacham Blvd., Room 663, Fort 

Worth Texas 76137. 

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 AD, any 

incorporated-by-reference service 

information, the economic evaluation, 

any comments received, and other 

information. The street address for the 

Docket Operations Office (phone: 800– 

647–5527) is U.S. Department of 

Transportation, Docket Operations 

Office, M–30, West Building Ground 

Floor, Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Michael Kohner, Aerospace Engineer, 

Rotorcraft Certification Office, 

Rotorcraft Directorate, FAA, 2601 

Meacham Blvd., Fort Worth, TX 76137; 

telephone (817) 222–5170; email 7-avsasw-170@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On May 28, 2013, at 78 FR 31863, the 

Federal Register published our notice of 

proposed rulemaking (NPRM), which 

proposed to amend 14 CFR part 39 by 

adding an AD that would apply to 

Sikorsky Model CH–54A helicopters, 

now under the Erickson Air-Crane 

Incorporated (Erickson) Model S–64E 

type certificate. The NPRM proposed to 

supersede AD 97–19–10 (62 FR 47933, 

September 12, 1997), which required 

inspecting and reworking the MGB 

assembly plate. Since AD 97–19–10 was 

issued, further analysis was performed 

by the current type certificate holder. As 

a result, the NPRM proposed to 

establish or revise the life limit for 

various parts, to remove various parts 

from service, to require various 

inspections and other maintenance 

actions, and to revise the component 

history card or equivalent record and 

the airworthiness limitations section of 

the maintenance manual accordingly. 

The proposed requirements were 

intended to prevent a crack in a flight 

critical component, failure of a critical 

part, and subsequent loss of control of 

the helicopter. 

Comments 

We gave the public the opportunity to 

participate in developing this AD, but 

we did not receive any comments on the 

NPRM (78 FR 31863, May 28, 2013). 

FAA’s Determination 

We have reviewed the relevant 

information and determined that an 

unsafe condition exists and is likely to 

exist or develop on other products of 

these same type designs and that air 

safety and the public interest require 


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65164 Federal Register / Vol. 78, No. 211 / Thursday, October 31, 2013 / Rules and Regulations 

adopting the AD requirements as 

proposed. 

Related Service Information 

Erickson Service Bulletin (SB) No. 

64B General-1, Revision 19, dated 

September 15, 2010 (SB 64B General-1), 

specifies the retirement life for certain 

parts and assemblies as well as noting 

other maintenance actions. This and the 

previous revisions of SB 64B General-1 

contain reduced or new life limits for 

certain parts, parts which should be 

removed from service, other 

maintenance actions, and various other 

provisions for certain parts. We have 

also reviewed Erickson SB No. 64B10– 

3, Revision D, dated October 15, 2007, 

which provides ultrasonic inspection 

procedures for the Main Rotor (M/R) 

hub horizontal hinge pins. 

Differences Between This AD and the 

Service Information 

This AD contains only those parts for 

the Model S–64E helicopters whose life 

limit has either been reduced or added 

for an existing P/N, whereas SB 64B 

General-1 also contains parts whose life 

limits have been extended. As a result, 

this proposed AD does not include all 

of the parts or P/Ns that are listed in SB 

64B General-1. 

Costs of Compliance 

We estimate that this AD will affect 

13 helicopters of U.S. registry, and the 

proposed actions will take the following 

number of estimated work hours to 

accomplish: 

• 26 work hours (2 work hours per 

helicopter) for the fleet to review the 

helicopter records or to remove a part to 

determine if an affected part is installed; 

• 845 work hours (65 work hours per 

helicopter) for the fleet to replace the 

parts or assemblies on or before 

reaching the retirement lives stated in 

Table 1 of the AD, assuming an annual 

usage of 600 hours TIS; 

• 287 work hours per helicopter to 

replace all the parts or assemblies listed 

in Table 2 of the AD; 

• 130 work hours (10 work hours per 

helicopter) for the fleet to inspect the M/ 

R servo housing assemblies for an oil 

leak, assuming each inspection would 

take approximately 0.25 work hour per 

helicopter and would be accomplished 

40 times annually; 

• Approximately 293 work hours 

(22.5 work hours per helicopter) for the 

fleet to UT inspect each M/R hub 

horizontal hinge pin, assuming that 

each inspection would take 7.5 work 

hours per helicopter and would be 

accomplished 3 times annually; 

• 288 work hours (48 work hours per 

helicopter) to perform an MPI of each 

main gearbox second stage lower 

planetary plate and second stage 

planetary plate assembly assuming 6 

helicopters would be inspected 

annually; 

• 192 work hours (32 work hours per 

helicopter) to perform an MPI of each 

M/R shaft and M/R shaft assembly, 

assuming 6 helicopters would be 

inspected annually, and 

• 96 work hours (32 work hours per 

helicopter) to perform an FPI of each M/ 

R tandem servo housing assembly, 

assuming 3 helicopters would be 

inspected annually. 

Therefore, we estimate that it will 

take approximately 2,157 work hours to 

accomplish the proposed actions at a 

cost of $183,345, using an average labor 

rate $85 per work hour. Replacement 

parts will cost approximately: 

• $5,363,449 ($412,573 per 

helicopter) to replace the parts or 

assemblies on the entire fleet on or 

before reaching the proposed retirement 

lives, assuming parts for 13 helicopters 

would require replacement; and 

• $2,594,400 per helicopter to replace 

the parts or assemblies that are listed in 

Table 2 of the AD. 

Using these assumptions, the 

estimated total cost for the required 

parts will be approximately $7,957,849. 

Based on these estimated amounts using 

these assumptions, we estimate the total 

cost impact of the AD on the U.S. 

operators will be $8,141,194. 

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 

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 to the extent that it justifies 

making a regulatory distinction; 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 an economic evaluation 

of the estimated costs to comply with 

this 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. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by 

removing Airworthiness Directive (AD) 

97–19–10, Amendment 39–10130 (62 

FR 47933, September 12, 1997), and 

adding the following new AD: 

2013–20–15 SIKORSKY AIRCRAFT 

CORPORATION-MANUFACTURED 

(SIKORSKY) MODEL HELICOPTERS 

(TYPE CERTIFICATE CURRENTLY 

HELD BY ERICKSON AIR-CRANE 

INCORPORATED): Amendment 39– 

17621; Docket No. FAA–2013–0454; 

Directorate Identifier 2009–SW–81–AD. 

(a) Applicability 

This AD applies to Sikorsky Model CH– 

54A helicopters, now under the Erickson AirCrane Incorporated (Erickson) Model S–64E 

type certificate, certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as 

fatigue cracking in a flight critical 

component, failure of the component, and 

subsequent loss of control of the helicopter. 

(c) Affected ADs 

This AD supersedes AD 97–19–10, 

Amendment 39–10130 (62 FR 47933, 

September 12, 1997). 


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Federal Register / Vol. 78, No. 211 / Thursday, October 31, 2013 / Rules and Regulations 65165 

(d) Effective Date 

This AD becomes effective December 5, 

2013. 

(e) Compliance 

You are responsible for performing each 

action required by this AD within the 

specified compliance time unless it has 

already been accomplished prior to that time. 

(f) Required Actions 

(1) Before further flight, for each part listed 

in Table 1 to paragraph (f) of this AD: 

(i) Remove any part that has reached or 

exceeded its newly established or revised 

retirement life. 

(ii) Record the newly established or revised 

retirement life for each part on the 

component history card or equivalent record. 

(iii) Make pen and ink changes or insert a 

copy of this AD into the Airworthiness 

Limitations section of the maintenance 

manual to establish or revise the retirement 

life for each part that is listed in Table 1 to 

paragraph (f) of this AD. 

TABLE 1 TO PARAGRAPH (F) OF THIS AD—PARTS WITH NEW OR REVISED LIFE LIMITS

Part name Part No. (P/N) Retirement life 

Rod and bushing assembly, main rotor (M/R) ... 6410–21090–012 ............................................. 5,700 hours time-in-service (TIS) or 60 

months since the initial installation on any 

helicopter, whichever occurs first. 

Rod and bushing assembly, M/R ....................... 6410–21090–013 or –014 ................................ 5,700 hours TIS. 

Lower plate, M/R hub ......................................... 6410–23009–102 ............................................. 3,000 hours TIS. 

Upper plate, M/R hub ......................................... 6410–23011–102 ............................................. 3,000 hours TIS. 

Swashplate, rotating, M/R .................................. 6410–24002–101 ............................................. 12,860 hours TIS. 

Piston rod ........................................................... 6410–26005–104 ............................................. 10,500 hours TIS. 

Cylinder, damper assembly ................................ 6410–26215–101 ............................................. 7,300 hours TIS. 

M/R blade ........................................................... 6415–20201–045 or –047 ................................ 3,300 hours TIS. 

M/R blade ........................................................... 6415–20201–048, –049, –050, or –051 .......... 20,000 hours TIS. 

Truss assembly, stabilizer .................................. 6420–66250–041 ............................................. 4,720 hours TIS. 

M/R shaft assembly (includes shaft, P/N 6435– 

20078–104).

6435–20078–014 or –015 ................................ 2,600 hours TIS. 

M/R shaft assembly (includes shaft, P/N 6435– 

20078–105).

6435–20078–016 ............................................. 5,000 hours TIS. 

Second stage planetary plate assembly, main 

gearbox assembly.

6435–20231–012, –014, or –015 .................... 1,300 hours TIS. 

Second stage planetary plate assembly, main 

gearbox assembly.

6435–20231–016 ............................................. 2,600 hours TIS. 

Oil cooler and support assembly ........................ 6435–60050–044 ............................................. 9,885 hours TIS. 

Tail rotor (T/R) blade .......................................... 65160–00001–042, –045, or –048 .................. 23,300 hours TIS. 

T/R blade ............................................................ 65161–00001–042 ........................................... 23,300 hours TIS. 

Hub, M/R ............................................................ S1510–23001–005 ........................................... 3,000 hours TIS. 

Spindle assembly, M/R ...................................... S1510–23027–5 ............................................... 5,675 hours TIS. 

Horn assembly, M/R ........................................... S1510–23350–4, –6, or –8 .............................. 9,710 hours TIS. 

Sleeve, M/R ........................................................ S1510–23351–2 ............................................... 12,930 hours TIS. 

Sleeve lockwasher, M/R ..................................... S1510–23458–0 ............................................... 2,700 hours TIS. 

Cuff, M/R blade .................................................. S1515–20320–0 ............................................... 6,410 hours TIS. 

Cuff, M/R blade .................................................. S1515–20320–001 or –002 ............................. 12,930 hours TIS. 

Piston assembly, M/R tandem servo ................. S1565–20443–0 or S1565–20443–301 ........... 8,100 hours TIS. 

Fork assembly, M/R tandem servo .................... S1565–20449 or S1565–20449–301 ............... 8,100 hours TIS. 

Bearing, T/R drive shaft ..................................... SB1111–004 or –601 ....................................... 1,000 hours TIS or 12 months while installed 

on any helicopter, whichever occurs first. 

Note to Table 1 to paragraph (f) of this AD: The list of parts in Table 1 to paragraph (f) of this AD contains only a portion of the life-limited 

parts for this model helicopter and is not an all-inclusive list. 

(2) Before further flight, remove from 

service any part with a P/N listed in Table 

2 to Paragraph (f) of this AD, regardless of the 

part’s TIS. The part numbers listed in Table 

2 to paragraph (f)(2) of this AD are not 

eligible for installation on any helicopter. 

TABLE 2 TO PARAGRAPH (F) OF THIS AD—PARTS TO BE REMOVED FROM SERVICE

Part name P/N 

Rod and bushing assembly, M/R .......................................................................................................................... 6410–21090–011. 

M/R blade .............................................................................................................................................................. 6415–20001–013, –014, or –015. 

Pylon stabilizer ....................................................................................................................................................... 6420–66201–010, –014, or –015. 

M/R shaft assembly ............................................................................................................................................... 6435–20078–013. 

Oil cooler and support assembly ........................................................................................................................... 6435–60050–043. 

Pitch change link, rotary rudder ............................................................................................................................ 65113–07100–046. 

Spindle, M/R blade ................................................................................................................................................ S1510–23070–3. 

(3) Within 20 hours TIS, and thereafter at 

intervals not to exceed 20 hours TIS, visually 

inspect each M/R servo and control arm 

assembly, P/N S1565–20421–10, –11, –041, 

or –043, and determine if there is any oil 

leaking from the M/R tandem servo housing 

assembly (servo housing), P/N S1565–20252– 

2. If there is any oil leaking from the servo 

housing, before further flight, replace the 

M/R servo and control arm assembly. 

(4) Within 20 hours TIS or before reaching 

1,120 hours TIS, whichever occurs later, and 

thereafter at intervals not to exceed 200 hours 

TIS or 12 months, whichever occurs first, 

ultrasonic (UT) inspect each M/R hub 

horizontal hinge pin (hinge pin), P/N S1510– 

23099–1 or P/N S1510–23099–001, for a 

crack in accordance with the 


wreier-aviles on DSK5TPTVN1PROD with RULES
65166 Federal Register / Vol. 78, No. 211 / Thursday, October 31, 2013 / Rules and Regulations 

Accomplishment Instructions, paragraphs 

2.A through 2.C, of Erickson Service Bulletin 

No. 64B10–3, Revision D, dated October 15, 

2007, except you are not required to contact 

Erickson nor send hinge pins to them. A nondestructive testing (NDT) UT Level I Special, 

Level II, or Level III inspector who is 

qualified under the guidelines established by 

ASNT SNT–TC–1A, ISO 9712, or an FAAaccepted equivalent qualification standard 

for NDT inspection and evaluation, must 

perform the UT inspection. 

(5) Within 150 hours TIS or before reaching 

1,450 hours TIS, whichever occurs later, 

perform a fluorescent-magnetic particle 

inspection (MPI) of each second stage 

planetary plate assembly, P/N 6435–20231– 

016, for a crack. 

(6) Within 150 hours TIS or before reaching 

1,450 hours TIS, whichever occurs later, and 

thereafter at intervals not to exceed 650 hours 

TIS, perform an MPI of each M/R shaft, P/ 

N 6435–20078–104, for a crack, paying 

particular attention to the lower spline area. 

(7) Within 150 hours TIS or before reaching 

1,450 hours TIS, whichever occurs later, and 

thereafter at intervals not to exceed 1,450 

hours TIS, perform an MPI of each M/R shaft, 

P/N 6435–20078–105, for a crack, paying 

particular attention to the lower spline area. 

(8) Within 150 hours TIS or before reaching 

3,375 hours TIS, whichever occurs later, and 

thereafter at intervals not to exceed 3,375 

hours TIS, perform a fluorescent penetrant 

inspection of each housing lug on each servo 

housing, P/N S1565–20252–2, for a crack. 

(9) At each overhaul of the main gearbox 

assembly, P/N 6435–20400–053, –054, –058, 

–060, –062, –063, –064, –065, or –066, 

perform an MPI of the entire shaft of each 

M/R shaft assembly, P/N 6435–20078–014, 

–015, or –016, for a crack, paying particular 

attention to the rotating swashplate spherical 

bearing ball travel area, which is located 

approximately ten inches above the upper 

roller bearing journal shoulder. 

(10) If there is a crack in any part, before 

further flight, replace the cracked part. 

(11) At each overhaul of the damper 

assembly, P/N 6410–26200–042, replace the 

following parts with airworthy parts that 

have zero (0) hours TIS: 

(i) All Air Force-Navy Aeronautical 

Standard (AN), Aerospace Standard (AS), 

Military Standard (MS), and National 

Aerospace Standard (NAS) nuts, bolts, 

washers, and packings, except packing, P/N 

MS28775–011, installed on stud, P/N 

SHF111–11SN–12A; 

(ii) Lock washer, P/N SS5073–2; 

(iii) Nut, P/N SS5081–05; 

(iv) Felt seal, P/N S1510–26017; 

(v) Retaining ring, P/N UR106L; and 

(vi) Nut, P/N 6410–26214–101. 

(g) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Rotorcraft Certification 

Office, FAA, may approve AMOCs for this 

AD. Send your proposal to: Michael Kohner, 

Aerospace Engineer, Rotorcraft Certification 

Office, Rotorcraft Directorate, FAA, 2601 

Meacham Blvd., Fort Worth, TX 76137; 

telephone (817) 222–5170; email 7-avs-asw170@faa.gov. 

(2) For operations conducted under a 14 

CFR part 119 operating certificate or under 

14 CFR part 91, subpart K, we suggest that 

you notify your principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office or 

certificate holding district office before 

operating any aircraft complying with this 

AD through an AMOC. 

(h) Additional Information 

Erickson Service Bulletin No. 64B General– 

1, Revision 19, dated September 15, 2010, 

which is not incorporated by reference, 

contains additional information about the 

subject of this AD. For service information 

identified in this AD, contact Erickson AirCrane Incorporated, ATTN: Chris Erickson, 

Director of Regulatory Compliance, 3100 

Willow Springs Rd., P.O. Box 3247, Central 

Point, OR 97502, telephone (541) 664–5544, 

fax (541) 664–2312, email address cerickson@

ericksonaircrane.com. You may review a 

copy of this information at the FAA, Office 

of the Regional Counsel, Southwest Region, 

2601 Meacham Blvd., Room 663, Fort Worth, 

Texas 76137. 

(i) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6200: Main Rotor System; 6300: Main 

Rotor Drive System; 6410: Tail Rotor Blades; 

6500: Tail Rotor Drive System. 

(j) 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. 

(i) Erickson Service Bulletin No. 64B10–3, 

Revision D, dated October 15, 2007. 

(ii) Reserved. 

(3) For Erickson service information 

identified in this AD, contact Erickson AirCrane Incorporated, ATTN: Chris Erickson, 

Director of Regulatory Compliance, 3100 

Willow Springs Rd, P.O. Box 3247, Central 

Point, OR 97502, telephone (541) 664–5544, 

fax (541) 664–2312, email address cerickson@

ericksonaircrane.com. 

(4) You may view this service information 

that is incorporated by reference at FAA, 

Office of the Regional Counsel, Southwest 

Region, 2601 Meacham Blvd., Room 663, Fort 

Worth, Texas 76137. 

(5) You may also 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 Fort Worth, Texas, on September 

25, 2013. 

Lance T. Gant, 

Acting Directorate Manager, Rotorcraft 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–24955 Filed 10–30–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0625; Directorate 

Identifier 2013–NM–013–AD; Amendment 

39–17638; AD 2013–22–06] 

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) 94–13–06 

for certain The Boeing Company Model 

747 series airplanes. AD 94–13–06 

required repetitive detailed inspections 

to detect cracking in certain fuselage 

upper deck tension ties, repair or 

modification of any cracked tension ties, 

and repetitive inspections of repaired 

and modified tension ties and repair or 

modification if necessary. AD 94–13–06 

also provided for optional terminating 

action for the repetitive detailed 

inspections of tension ties that had not 

been repaired or modified. This new AD 

retains the repetitive inspections, 

mandates the previously optional 

terminating modification, and adds, for 

tension ties that have not been repaired 

or modified, repetitive inspections that 

must be done concurrently with the 

existing repetitive inspections. This AD 

was prompted by an evaluation by the 

design approval holder indicating that 

the upper deck tension ties of the 

fuselage are subject to widespread 

fatigue damage. We are issuing this AD 

to prevent widespread fatigue damage of 

certain fuselage upper deck tension ties, 

which could result in reduced structural 

integrity of the airplane. 

DATES: This AD is effective December 5, 

2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of December 5, 2013. 

ADDRESSES: For service information 

identified in this AD, contact, 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 view this referenced service 

information at the FAA, Transport 

Airplane Directorate, 1601 Lind Ave. 

SW., Renton, Washington. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 


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