[4910-13-Pj

DEPARTMENT OF TRANSPORT AnON Federal Aviation Administration 14CFR Part 39 

# .G0%- 00 1/ ,~!.~:!11 rDocket No. FAA-10IO-++++j ~irectorate Identifier 2010-NM-142-ADj Amendmen ..,.-

### 1.0,.' 

## 'I 

# JI - 

# ;?l7fb~
_ 

# l'i-.IlL ~;.

# "<>","'" 3 ~'; AD *"1 

## 0I.010--rs--E8'- 7 7 10- RIN 2120-AA64 

# I 

# M::"~ Airworthiness Directivesj The Boemg Company Model 767-200, -300, and -300F IG /~ 0-01' 

# I -:1{lt: Series Airplanes Powered by General Electric or Pratt & Whitney Engines AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. SUMMARY: The FAA is superseding an existing airworthiness directive (AD) that applies to certain Model 767-200, -300, and -300F series airplanes. The existing AD currently requires repetitive inspections to dete

# J\ discrepancies ofti,e eight aft-most fastener holes inthe horizontal tangs ofthe midspar fitting ofthe strut, and corrective actions ifnecessary. The existing AD also requrres repetitive inspections for cracks of closeout angle that covers the two aft-most fastLers inthe lower tang of the midspar fitting, and related investigative and corrective ~ctions ifnecessary, The existing AD al AAI""'·- IZ INml\l.$/SIG r. ,"'::>1'%10"= 

### 'P':
~~ 

## 1

. DATe--; provides an optional terminating action forthe repetitive inspections, This new AD IrtiM..... 

### loBs

, r<lJllA~5[G - i?~ II II \, r ( ..iI,',' reduces the compliance times for doing the ins~ections, This AD results from reports 0' I\)'L.'\-,~ fr,i;: •... "" ,I DATE cracks inthe midspar fitting tangs, We are issUl'ngthis AD to detect and correct fatigue 

## ? 7 

# tv

~~~ cracking inthe primary strut structure and reduced structural integrity ofthe strut, whic - 

# I .. mAtS/5IG could result in separation ofthe strut and enginer" r 

## C.~ '" DATES: This AD hecomes effective [INSER~ DATE 15DAYS AFTER DATE OF 

# ~'1.!21' ? PUBLICATION INTHE FEDERAL REGISTER]. - 

# /I'f 

# 7i?J71'q,

_ m 

# 7 

# q ID Joe 

## cdt~,?etl'( -11)0/-/0 

### I[4910-13-PJ

DEPARTMENT OF TRANSPORT AnON Federal Aviation Administration 14 CFR Part 39 _ON(URRENCES oun"G sYMBOL 1'<IllAL5J51(; [Docket No. FAA-10lO-++++; Directorate Identifier 2010-NM-142-AD; Amendmen 

## J: LoCJt"Joh 

## I ,n ·39-**; AD **) 7 7 

# '0

ACTION: Final rule; request for comments. RIN 2120-AA64 

# I Airworthiness Directives; The Boeing CompJy Model 767~200, -300, and -300F Series Airplanes Powered by General Electric or Pratt &Whitney Engines AGENCY: Federal Aviation Administration (FAA), Department ofTransportation (DOT). I SUMMARY: The FAA is superseding an existIng airworthiness directive (AD)that



# -- - I applies to certain Model 767-200, -300, and -300F series airplanes. The existing AD currently requires repetitive inspections to detect discrepancies ofthe eight aft-most O<ITI'fG SYM£lOL /JJJm- (/.oS

AAl1"1~ IZ INI71.Al.${SIG r. t"''''''=v~ 

# -p: OATE 

## 1 

# ...,! 

# ;":~';7f4J ~1T1AlS/SIG 

## 1)

OUTTNG SYMeOL



### - /0 

## I 

# :~ fastener holes in the horizontal tangs ofthe midspar fitting of the strut. and corrective actions ifnecessary. The existing AD also reqUi~eSrepetitive inspections for cracks oft closeout angle that covers the two aft-most fastdners in the lower tang ofthe midspar fining, and related investigative and corrective Jctions ifnecessary. The existing AD al
~ 

# ~- provides an optional terminating acrion forthe repetitive inspections. This new AD ~1T1Al..S/SIG reduces the compliance times for doing the inspections. This AD results from reports 0 

# I .n cracks inthe midspar fitting tangs. We are issuing this AD to detect and correct fatigue cracking inthe primary strut structure and redu1ed structural integrity ofthc strut, whic could result in separation ofthe strut and engine. ' DATES: This AD becomes effective [INSERT DATE 15 DAYS AFTER DATE OF PUBLICAnON IN THE FEDERAL REGISTER). 

# ..,

## r,/'7 /0 

# ~;o 

# ·AK~;


# .., 

# 71.10