(6)
 The following observations are acceptable:

 (a)
 Leading edge nicks (9).

 (b)
 Blade discoloration (8).

 (7)
 The following observations are not acceptable, the observations are criteria for APU removal:

 (a)
 Cracked, bent or missing vanes not permitted (10),(13),(12).

 (b)
 Impact damage to all vane tips against adjacent shaft is indication of rotor imbalance, APU should be removed in this case (11).

 (8)
 Push inlet guide vane linkage, by hand, into the engine assembly until the linkage stops and the inlet guide vanes are fully open.

 (9)
 Put the optic fiber borescope through the compressor inlet duct and perforated inlet housing to the inlet guide vanes.

 (10)
 Examine the guide vanes for evidence of damage.
 (Ref. Fig. 606/TASK 49-20-00-991-020)

R  EFF : 001-049, 101-105, 107-107, 151-199, 49-20-00Page 609 201-210, Config-3 Aug 01/05
 CES

 Clevis Assembly and Attaching Bolt
 Figure 604/TASK 49-20-00-991-018

 CES

 Inlet Guide Vane (IGV) Damge Criteria (IGV closed)
 Figure 605/TASK 49-20-00-991-019

 CES

 Inlet Guide Vane (IGV) Damage Criteria (IGV open)
 Figure 606/TASK 49-20-00-991-020

 CES

 (11)
 The following observations are acceptable:

 (a)
 Leading edge nicks (15).

 (b)
 Blade discoloration (14).

 (12)
 The following observations are not acceptable, the observations are criteria for APU removal:

 (a)
 Cracked, bent or missing vanes not permitted (16),(17),(18).

 (b)
 Impact damage to all vane tips against adjacent shaft is indication of rotor imbalance, APU should be removed in this case (19).

 Subtask 49-20-00-960-056
 D. Examine the Load Compressor Impeller leading edge for damage. NOTE : MAKE SURE THE APU INTERNAL TEMPERATURE IS NOT MORE THAN 176F (80C)
____ BEFORE THE BORESCOPE IS PUT INTO THE APU. HEAT CAN DAMAGE THE BORESCOPE. MAKE SURE THE BORESCOPE CLEARS THE COMPRESSOR IMPELLER BLADES BEFORE THE APU IS ROTATED. ROTATION OF THE APU ROTATING GROUP CAN DAMAGE THE BORESCOPE.
 (1)
 Push the borescope past the inlet guide vanes to examine the load compressor leading edges.

 (2)
 Prepare to turn rotating group to examine the load compressor impeller.

 (a)
 Remove cap on end of starter.

 (b)
 Insert a 1/4 inch hex socket, with attached 6 inch extension and ratchet wrench, onto the 1/4 inch hex shaft on the end of the starter.

 (3)
 Turn the rotating group as necessary and examine the load compressor impeller leading edges. (Ref. Fig. 607/TASK 49-20-00-991-021)

R  EFF : 001-049, 101-105, 107-107, 151-199, 49-20-00Page 613 201-210, Config-3 Aug 01/05
 CES

 Load-Compressor Impeller Leading-Edge Damage Criteria Figure 607/TASK 49-20-00-991-021

R  EFF : 001-049, 101-105, 107-107, 151-199, 49-20-00Page 614 201-210, Config-3 Aug 01/05
 CES

 (4)
 The following observations are acceptable:

 (a)
 Bent inducer blade tips are permitted on one blade only (20).

 (b)
 Leading edge nicks and rough edges due to erosion is acceptable without significantly displaced material (21).

 (c)
 Blade discoloration is acceptable (22).

 (5)
 The following observations are not acceptable, the observations are criteria for APU removal:

 (a)
 Remove the APU if visible cracks (24) of the leading edge , fillets, hub are observed or visible pieces are missing (23).

 (b)
 Remove APU if multiple blades are bent (25).

 (6)
 Remove optic fiber borescope from the compressor inlet duct.

 (7)
 Install the bolt that holds the inlet guide vane actuator (IGVA) and clevis assemblies together (Ref. TASK 49-23-51-400-004).

 (8)
 Rotate cover plate counterclockwise to close clevis assembly acces opening and TORQUE bolts to to 0.57 m.daN (50.44 lbf.in).

 (9)
 Install cap on end of starter. Subtask 49-20-00-960-057

 E.
 Examine the engine compressor impeller for damage.

 (1)
 Prepare to turn the rotating group to examine engine compressor impeller blades.
　
中國航空網(wǎng) m.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：A320飛機(jī)維護(hù)手冊 AMM 機(jī)載輔助動(dòng)力 AIRBORNE AUXILIARY POWER3(91)